WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il) Reynolds number: 1,000,000 Max Cl/Cd: 68.95 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-whitcomb-il-1000000.txt Download as CSV file: xf-whitcomb-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.750 -0.9413 0.13292 0.13051 -0.0271 1.0000 0.0195
-18.500 -1.0038 0.11544 0.11280 -0.0370 1.0000 0.0194
-18.250 -1.0457 0.10325 0.10042 -0.0440 1.0000 0.0194
-18.000 -1.0762 0.09376 0.09077 -0.0493 1.0000 0.0194
-17.750 -1.1003 0.08571 0.08257 -0.0538 1.0000 0.0194
-17.500 -1.1205 0.07863 0.07536 -0.0576 1.0000 0.0194
-17.250 -1.1369 0.07245 0.06904 -0.0608 1.0000 0.0194
-17.000 -1.1501 0.06707 0.06354 -0.0634 1.0000 0.0194
-16.750 -1.1634 0.06202 0.05836 -0.0655 1.0000 0.0195
-16.500 -1.1810 0.05676 0.05295 -0.0673 1.0000 0.0195
-16.250 -1.1947 0.05242 0.04848 -0.0682 1.0000 0.0197
-16.000 -1.2048 0.04882 0.04476 -0.0685 1.0000 0.0198
-15.750 -1.2123 0.04578 0.04163 -0.0683 1.0000 0.0199
-15.500 -1.2179 0.04316 0.03892 -0.0677 1.0000 0.0200
-15.250 -1.2222 0.04090 0.03659 -0.0667 1.0000 0.0201
-15.000 -1.2247 0.03893 0.03455 -0.0655 1.0000 0.0202
-14.750 -1.2265 0.03715 0.03271 -0.0640 1.0000 0.0204
-14.500 -1.2271 0.03557 0.03107 -0.0623 1.0000 0.0205
-14.250 -1.2265 0.03416 0.02961 -0.0606 1.0000 0.0206
-14.000 -1.2259 0.03285 0.02824 -0.0586 1.0000 0.0208
-13.750 -1.2244 0.03168 0.02702 -0.0565 1.0000 0.0210
-13.500 -1.2237 0.03056 0.02586 -0.0541 1.0000 0.0211
-13.250 -1.2240 0.02951 0.02475 -0.0514 1.0000 0.0213
-13.000 -1.2274 0.02853 0.02371 -0.0481 1.0000 0.0214
-12.750 -1.2350 0.02765 0.02278 -0.0438 1.0000 0.0215
-12.500 -1.2209 0.02656 0.02162 -0.0436 0.9994 0.0218
-12.250 -1.1982 0.02548 0.02048 -0.0448 0.9982 0.0220
-12.000 -1.1751 0.02449 0.01942 -0.0459 0.9971 0.0223
-11.750 -1.1504 0.02358 0.01844 -0.0472 0.9961 0.0226
-11.500 -1.1240 0.02277 0.01756 -0.0486 0.9953 0.0228
-11.250 -1.0969 0.02187 0.01660 -0.0501 0.9946 0.0230
-11.000 -1.0697 0.02058 0.01526 -0.0523 0.9940 0.0237
-10.750 -1.0456 0.01972 0.01438 -0.0531 0.9927 0.0241
-10.500 -1.0185 0.01906 0.01370 -0.0543 0.9915 0.0246
-10.250 -0.9902 0.01847 0.01307 -0.0555 0.9905 0.0251
-10.000 -0.9613 0.01790 0.01248 -0.0567 0.9897 0.0257
-9.750 -0.9317 0.01739 0.01192 -0.0580 0.9890 0.0263
-9.500 -0.9015 0.01695 0.01145 -0.0593 0.9883 0.0268
-9.250 -0.8701 0.01615 0.01063 -0.0613 0.9878 0.0279
-9.000 -0.8388 0.01571 0.01019 -0.0628 0.9873 0.0289
-8.750 -0.8073 0.01534 0.00982 -0.0642 0.9868 0.0299
-8.500 -0.7756 0.01502 0.00946 -0.0656 0.9864 0.0309
-8.250 -0.7430 0.01451 0.00894 -0.0673 0.9861 0.0323
-8.000 -0.7107 0.01414 0.00859 -0.0689 0.9858 0.0338
-7.750 -0.6784 0.01388 0.00832 -0.0702 0.9855 0.0353
-7.500 -0.6455 0.01357 0.00799 -0.0718 0.9852 0.0370
-7.250 -0.6119 0.01321 0.00766 -0.0735 0.9850 0.0392
-7.000 -0.5784 0.01300 0.00745 -0.0750 0.9847 0.0412
-6.750 -0.5442 0.01270 0.00716 -0.0768 0.9845 0.0438
-6.500 -0.5104 0.01247 0.00695 -0.0784 0.9843 0.0466
-6.250 -0.4769 0.01227 0.00676 -0.0799 0.9841 0.0494
-6.000 -0.4429 0.01202 0.00656 -0.0816 0.9840 0.0534
-5.750 -0.4126 0.01178 0.00633 -0.0824 0.9832 0.0577
-5.500 -0.3836 0.01151 0.00611 -0.0830 0.9821 0.0634
-5.250 -0.3514 0.01127 0.00593 -0.0842 0.9815 0.0729
-5.000 -0.3184 0.01104 0.00577 -0.0856 0.9808 0.0842
-4.750 -0.2845 0.01081 0.00562 -0.0872 0.9803 0.0981
-4.500 -0.2497 0.01056 0.00548 -0.0890 0.9799 0.1163
-4.250 -0.2150 0.01033 0.00537 -0.0908 0.9797 0.1388
-4.000 -0.1791 0.01007 0.00526 -0.0929 0.9796 0.1684
-3.750 -0.1428 0.00982 0.00516 -0.0951 0.9795 0.2042
-3.500 -0.1056 0.00956 0.00506 -0.0975 0.9795 0.2428
-3.250 -0.0614 0.00908 0.00487 -0.1016 0.9795 0.3158
-3.000 -0.0014 0.00813 0.00447 -0.1096 0.9812 0.4638
-2.750 0.0472 0.00762 0.00451 -0.1144 0.9807 0.6160
-2.500 0.0897 0.00748 0.00436 -0.1170 0.9760 0.6391
-2.250 0.1375 0.00739 0.00429 -0.1205 0.9730 0.6489
-2.000 0.1664 0.00729 0.00416 -0.1203 0.9672 0.6545
-1.750 0.2061 0.00709 0.00399 -0.1222 0.9635 0.6577
-1.500 0.2466 0.00697 0.00391 -0.1244 0.9616 0.6607
-1.250 0.2822 0.00691 0.00387 -0.1254 0.9581 0.6648
-1.000 0.3147 0.00671 0.00367 -0.1256 0.9498 0.6694
-0.750 0.3453 0.00656 0.00352 -0.1257 0.9417 0.6716
-0.500 0.3753 0.00645 0.00345 -0.1256 0.9300 0.6738
-0.250 0.4096 0.00647 0.00346 -0.1261 0.9003 0.6766
0.000 0.4179 0.00817 0.00374 -0.1213 0.5698 0.6786
0.250 0.4355 0.00911 0.00411 -0.1190 0.4266 0.6815
0.500 0.4582 0.00981 0.00444 -0.1177 0.3332 0.6854
0.750 0.4838 0.01030 0.00462 -0.1172 0.2620 0.6881
1.000 0.5088 0.01063 0.00473 -0.1166 0.2053 0.6896
1.250 0.5343 0.01095 0.00489 -0.1159 0.1656 0.6906
1.500 0.5611 0.01122 0.00500 -0.1156 0.1325 0.6914
1.750 0.5883 0.01145 0.00511 -0.1154 0.1083 0.6920
2.000 0.6154 0.01169 0.00525 -0.1151 0.0891 0.6928
2.250 0.6428 0.01191 0.00538 -0.1149 0.0744 0.6935
2.500 0.6706 0.01211 0.00551 -0.1148 0.0643 0.6941
2.750 0.6984 0.01233 0.00567 -0.1146 0.0570 0.6948
3.000 0.7265 0.01248 0.00580 -0.1146 0.0531 0.6955
3.250 0.7540 0.01273 0.00601 -0.1144 0.0490 0.6963
3.500 0.7821 0.01288 0.00616 -0.1143 0.0465 0.6971
3.750 0.8098 0.01313 0.00636 -0.1142 0.0435 0.6977
4.000 0.8378 0.01332 0.00655 -0.1141 0.0415 0.6984
4.250 0.8658 0.01350 0.00671 -0.1140 0.0394 0.6990
4.500 0.8928 0.01384 0.00702 -0.1137 0.0371 0.6996
4.750 0.9205 0.01403 0.00723 -0.1136 0.0359 0.7004
5.000 0.9481 0.01425 0.00744 -0.1134 0.0345 0.7011
5.250 0.9754 0.01452 0.00769 -0.1132 0.0332 0.7016
5.500 1.0015 0.01496 0.00813 -0.1127 0.0317 0.7020
5.750 1.0288 0.01519 0.00838 -0.1125 0.0310 0.7024
6.000 1.0558 0.01546 0.00866 -0.1122 0.0300 0.7027
6.250 1.0825 0.01575 0.00895 -0.1119 0.0292 0.7030
6.500 1.1086 0.01612 0.00931 -0.1115 0.0283 0.7033
6.750 1.1329 0.01674 0.00995 -0.1107 0.0273 0.7035
7.000 1.1603 0.01693 0.01017 -0.1106 0.0269 0.7043
7.250 1.1865 0.01724 0.01052 -0.1102 0.0263 0.7050
7.500 1.2122 0.01758 0.01090 -0.1097 0.0257 0.7056
7.750 1.2376 0.01796 0.01130 -0.1091 0.0253 0.7059
8.000 1.2626 0.01835 0.01171 -0.1085 0.0248 0.7063
8.250 1.2871 0.01881 0.01219 -0.1078 0.0243 0.7067
8.500 1.3096 0.01951 0.01292 -0.1068 0.0238 0.7070
8.750 1.3306 0.02044 0.01393 -0.1055 0.0234 0.7074
9.000 1.3546 0.02089 0.01444 -0.1047 0.0232 0.7078
9.250 1.3779 0.02140 0.01502 -0.1038 0.0229 0.7081
9.500 1.4006 0.02198 0.01566 -0.1028 0.0226 0.7085
9.750 1.4228 0.02259 0.01635 -0.1017 0.0224 0.7089
10.000 1.4443 0.02325 0.01708 -0.1005 0.0221 0.7093
10.250 1.4655 0.02391 0.01780 -0.0993 0.0218 0.7097
10.500 1.4861 0.02460 0.01856 -0.0980 0.0216 0.7100
10.750 1.5062 0.02528 0.01931 -0.0967 0.0213 0.7105
11.000 1.5259 0.02594 0.02002 -0.0953 0.0211 0.7111
11.250 1.5450 0.02660 0.02073 -0.0938 0.0208 0.7116
11.500 1.5627 0.02738 0.02156 -0.0921 0.0206 0.7121
11.750 1.5777 0.02841 0.02267 -0.0900 0.0204 0.7124
12.000 1.5893 0.02977 0.02413 -0.0875 0.0201 0.7128
12.250 1.5915 0.03213 0.02669 -0.0838 0.0199 0.7131
12.500 1.6029 0.03308 0.02776 -0.0812 0.0198 0.7134
12.750 1.6079 0.03400 0.02879 -0.0775 0.0197 0.7138
13.000 1.6140 0.03510 0.03000 -0.0742 0.0196 0.7141
13.250 1.6184 0.03639 0.03141 -0.0709 0.0195 0.7144
13.500 1.6212 0.03780 0.03296 -0.0676 0.0194 0.7147
13.750 1.6220 0.03943 0.03472 -0.0642 0.0194 0.7150
14.000 1.6214 0.04119 0.03662 -0.0610 0.0192 0.7153
14.250 1.6182 0.04325 0.03882 -0.0578 0.0192 0.7155
14.500 1.6126 0.04562 0.04134 -0.0549 0.0191 0.7158
14.750 1.6057 0.04825 0.04412 -0.0523 0.0190 0.7160
15.000 1.5955 0.05143 0.04745 -0.0503 0.0189 0.7162
15.250 1.5818 0.05528 0.05148 -0.0490 0.0189 0.7164
15.500 1.5660 0.05991 0.05629 -0.0490 0.0188 0.7166
15.750 1.5452 0.06597 0.06253 -0.0508 0.0188 0.7168
16.000 1.5190 0.07422 0.07100 -0.0554 0.0188 0.7170
16.250 1.4811 0.08655 0.08359 -0.0642 0.0189 0.7170
16.500 1.4075 0.10792 0.10532 -0.0794 0.0190 0.7168
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