WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il) Reynolds number: 500,000 Max Cl/Cd: 59.59 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-whitcomb-il-500000-n5.txt Download as CSV file: xf-whitcomb-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -1.0234 0.09783 0.09406 -0.0455 1.0000 0.0193
-17.250 -1.0514 0.08879 0.08485 -0.0505 1.0000 0.0193
-17.000 -1.0738 0.08103 0.07695 -0.0547 1.0000 0.0193
-16.750 -1.0917 0.07432 0.07009 -0.0583 1.0000 0.0194
-16.500 -1.1063 0.06847 0.06410 -0.0612 1.0000 0.0194
-16.250 -1.1180 0.06339 0.05889 -0.0635 1.0000 0.0195
-16.000 -1.1274 0.05898 0.05436 -0.0653 1.0000 0.0195
-15.750 -1.1348 0.05515 0.05042 -0.0664 1.0000 0.0196
-15.500 -1.1407 0.05180 0.04696 -0.0670 1.0000 0.0197
-15.250 -1.1455 0.04884 0.04390 -0.0671 1.0000 0.0198
-15.000 -1.1492 0.04623 0.04119 -0.0669 1.0000 0.0199
-14.750 -1.1522 0.04392 0.03879 -0.0662 1.0000 0.0200
-14.500 -1.1545 0.04183 0.03662 -0.0652 1.0000 0.0201
-14.250 -1.1560 0.03995 0.03465 -0.0640 1.0000 0.0203
-14.000 -1.1566 0.03823 0.03285 -0.0626 1.0000 0.0204
-13.750 -1.1570 0.03665 0.03118 -0.0609 1.0000 0.0205
-13.500 -1.1566 0.03521 0.02966 -0.0590 1.0000 0.0207
-13.250 -1.1559 0.03388 0.02826 -0.0570 1.0000 0.0209
-13.000 -1.1551 0.03266 0.02697 -0.0548 1.0000 0.0211
-12.750 -1.1549 0.03153 0.02577 -0.0522 1.0000 0.0213
-12.500 -1.1427 0.03034 0.02449 -0.0519 0.9990 0.0215
-12.250 -1.1289 0.02922 0.02327 -0.0518 0.9976 0.0218
-12.000 -1.1142 0.02818 0.02214 -0.0517 0.9961 0.0220
-11.750 -1.0962 0.02695 0.02086 -0.0524 0.9947 0.0223
-11.500 -1.0751 0.02585 0.01972 -0.0533 0.9937 0.0226
-11.250 -1.0554 0.02488 0.01871 -0.0537 0.9919 0.0230
-11.000 -1.0335 0.02401 0.01779 -0.0543 0.9903 0.0234
-10.750 -1.0099 0.02319 0.01692 -0.0550 0.9889 0.0238
-10.500 -0.9843 0.02240 0.01609 -0.0561 0.9877 0.0243
-10.250 -0.9573 0.02166 0.01529 -0.0574 0.9866 0.0249
-10.000 -0.9299 0.02097 0.01453 -0.0586 0.9858 0.0255
-9.750 -0.9019 0.02027 0.01379 -0.0599 0.9851 0.0261
-9.500 -0.8732 0.01960 0.01311 -0.0613 0.9845 0.0269
-9.250 -0.8437 0.01905 0.01254 -0.0627 0.9840 0.0277
-9.000 -0.8166 0.01852 0.01198 -0.0635 0.9832 0.0287
-8.750 -0.7920 0.01801 0.01143 -0.0637 0.9818 0.0296
-8.500 -0.7646 0.01748 0.01088 -0.0645 0.9806 0.0307
-8.250 -0.7357 0.01700 0.01041 -0.0656 0.9794 0.0320
-8.000 -0.7062 0.01659 0.00997 -0.0666 0.9785 0.0335
-7.750 -0.6764 0.01623 0.00957 -0.0676 0.9778 0.0349
-7.500 -0.6459 0.01576 0.00913 -0.0689 0.9771 0.0367
-7.250 -0.6152 0.01540 0.00876 -0.0700 0.9765 0.0385
-7.000 -0.5841 0.01508 0.00842 -0.0712 0.9760 0.0402
-6.750 -0.5526 0.01471 0.00807 -0.0725 0.9755 0.0423
-6.500 -0.5209 0.01439 0.00776 -0.0738 0.9751 0.0448
-6.250 -0.4889 0.01411 0.00748 -0.0751 0.9746 0.0475
-6.000 -0.4566 0.01381 0.00722 -0.0765 0.9743 0.0512
-5.750 -0.4240 0.01354 0.00697 -0.0778 0.9739 0.0557
-5.500 -0.3911 0.01328 0.00675 -0.0793 0.9736 0.0616
-5.250 -0.3575 0.01301 0.00655 -0.0809 0.9733 0.0695
-5.000 -0.3236 0.01275 0.00635 -0.0825 0.9730 0.0786
-4.750 -0.2896 0.01251 0.00617 -0.0841 0.9727 0.0890
-4.500 -0.2557 0.01228 0.00601 -0.0858 0.9725 0.1008
-4.250 -0.2253 0.01205 0.00585 -0.0866 0.9716 0.1142
-4.000 -0.1937 0.01181 0.00572 -0.0878 0.9708 0.1335
-3.750 -0.1608 0.01157 0.00558 -0.0892 0.9701 0.1553
-3.500 -0.1260 0.01130 0.00546 -0.0911 0.9696 0.1844
-3.250 -0.0904 0.01103 0.00534 -0.0932 0.9692 0.2174
-2.750 -0.0035 0.01007 0.00498 -0.1013 0.9709 0.3567
-2.500 0.0587 0.00906 0.00490 -0.1099 0.9728 0.5767
-2.250 0.0790 0.00936 0.00535 -0.1076 0.9679 0.6126
-2.000 0.1144 0.00932 0.00530 -0.1088 0.9637 0.6273
-1.750 0.1584 0.00897 0.00491 -0.1117 0.9574 0.6393
-1.500 0.1930 0.00883 0.00478 -0.1124 0.9494 0.6472
-1.250 0.2261 0.00867 0.00459 -0.1130 0.9413 0.6546
-0.250 0.3590 0.01007 0.00433 -0.1143 0.5082 0.6725
0.000 0.3776 0.01089 0.00470 -0.1121 0.3946 0.6749
0.250 0.4013 0.01141 0.00491 -0.1112 0.3192 0.6769
0.500 0.4272 0.01181 0.00505 -0.1107 0.2572 0.6787
0.750 0.4540 0.01217 0.00516 -0.1105 0.2054 0.6806
1.000 0.4822 0.01244 0.00525 -0.1106 0.1678 0.6823
1.250 0.5110 0.01266 0.00531 -0.1109 0.1388 0.6835
1.500 0.5398 0.01290 0.00539 -0.1111 0.1139 0.6846
1.750 0.5691 0.01310 0.00548 -0.1114 0.0974 0.6857
2.000 0.5967 0.01329 0.00560 -0.1113 0.0841 0.6863
2.250 0.6243 0.01349 0.00573 -0.1111 0.0728 0.6868
2.500 0.6519 0.01370 0.00588 -0.1110 0.0644 0.6872
2.750 0.6794 0.01391 0.00605 -0.1108 0.0580 0.6877
3.000 0.7069 0.01412 0.00624 -0.1106 0.0535 0.6883
3.250 0.7340 0.01437 0.00645 -0.1103 0.0493 0.6889
3.500 0.7616 0.01457 0.00666 -0.1101 0.0464 0.6894
3.750 0.7889 0.01482 0.00688 -0.1099 0.0436 0.6899
4.000 0.8163 0.01506 0.00712 -0.1097 0.0415 0.6904
4.250 0.8437 0.01530 0.00736 -0.1095 0.0395 0.6909
4.500 0.8708 0.01559 0.00763 -0.1093 0.0377 0.6914
4.750 0.8978 0.01588 0.00792 -0.1090 0.0361 0.6919
5.000 0.9249 0.01614 0.00820 -0.1087 0.0345 0.6924
5.250 0.9516 0.01643 0.00849 -0.1084 0.0331 0.6931
5.500 0.9779 0.01681 0.00885 -0.1080 0.0318 0.6938
5.750 1.0045 0.01712 0.00920 -0.1077 0.0308 0.6944
6.000 1.0310 0.01745 0.00955 -0.1073 0.0298 0.6950
6.250 1.0573 0.01779 0.00991 -0.1070 0.0288 0.6955
6.500 1.0833 0.01818 0.01031 -0.1065 0.0280 0.6960
6.750 1.1086 0.01866 0.01079 -0.1060 0.0272 0.6965
7.000 1.1342 0.01907 0.01125 -0.1055 0.0267 0.6970
7.250 1.1595 0.01950 0.01173 -0.1049 0.0260 0.6975
7.500 1.1845 0.01996 0.01223 -0.1044 0.0254 0.6979
7.750 1.2093 0.02043 0.01273 -0.1037 0.0249 0.6984
8.000 1.2337 0.02091 0.01325 -0.1031 0.0244 0.6988
8.250 1.2577 0.02144 0.01381 -0.1023 0.0240 0.6993
8.500 1.2806 0.02209 0.01448 -0.1014 0.0235 0.6998
8.750 1.3036 0.02270 0.01516 -0.1005 0.0231 0.7004
9.000 1.3267 0.02328 0.01582 -0.0996 0.0227 0.7009
9.250 1.3491 0.02391 0.01653 -0.0986 0.0223 0.7012
9.500 1.3709 0.02458 0.01727 -0.0975 0.0220 0.7015
9.750 1.3922 0.02528 0.01806 -0.0964 0.0217 0.7018
10.000 1.4130 0.02597 0.01883 -0.0952 0.0214 0.7022
10.250 1.4332 0.02669 0.01964 -0.0939 0.0211 0.7025
10.500 1.4526 0.02744 0.02046 -0.0925 0.0209 0.7029
10.750 1.4713 0.02822 0.02133 -0.0910 0.0207 0.7032
11.000 1.4888 0.02905 0.02225 -0.0893 0.0205 0.7036
11.250 1.5052 0.02994 0.02322 -0.0875 0.0203 0.7039
11.500 1.5198 0.03094 0.02430 -0.0855 0.0201 0.7043
11.750 1.5320 0.03210 0.02556 -0.0831 0.0199 0.7046
12.000 1.5419 0.03333 0.02691 -0.0804 0.0197 0.7050
12.250 1.5485 0.03442 0.02814 -0.0771 0.0196 0.7053
12.500 1.5553 0.03565 0.02952 -0.0740 0.0195 0.7057
12.750 1.5608 0.03699 0.03102 -0.0709 0.0194 0.7062
13.000 1.5646 0.03848 0.03268 -0.0678 0.0193 0.7067
13.250 1.5664 0.04014 0.03450 -0.0646 0.0192 0.7072
13.500 1.5662 0.04199 0.03652 -0.0614 0.0191 0.7076
13.750 1.5643 0.04404 0.03874 -0.0584 0.0190 0.7079
14.000 1.5601 0.04637 0.04125 -0.0557 0.0189 0.7082
14.250 1.5538 0.04903 0.04409 -0.0532 0.0188 0.7085
14.500 1.5445 0.05217 0.04741 -0.0512 0.0188 0.7088
14.750 1.5324 0.05591 0.05135 -0.0500 0.0187 0.7091
15.000 1.5173 0.06049 0.05613 -0.0500 0.0187 0.7093
15.250 1.4971 0.06656 0.06242 -0.0519 0.0186 0.7095
15.500 1.4717 0.07489 0.07100 -0.0567 0.0186 0.7096
15.750 1.4320 0.08815 0.08457 -0.0665 0.0187 0.7097
16.000 1.3455 0.11295 0.10977 -0.0837 0.0189 0.7093
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