NACA 63(2)-615 (naca632615-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(2)-615 (naca632615-il) Reynolds number: 500,000 Max Cl/Cd: 112.16 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca632615-il-500000.txt Download as CSV file: xf-naca632615-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)-615
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.6398 0.07428 0.07144 -0.0739 1.0000 0.0194
-14.000 -0.6825 0.06347 0.06040 -0.0816 1.0000 0.0193
-13.750 -0.7111 0.05628 0.05303 -0.0861 1.0000 0.0191
-13.500 -0.7340 0.05065 0.04722 -0.0892 1.0000 0.0192
-13.250 -0.7556 0.04582 0.04219 -0.0911 1.0000 0.0192
-13.000 -0.7711 0.04226 0.03845 -0.0917 1.0000 0.0193
-12.750 -0.7883 0.03911 0.03513 -0.0911 1.0000 0.0195
-12.500 -0.8045 0.03695 0.03284 -0.0890 1.0000 0.0196
-12.250 -0.8190 0.03523 0.03100 -0.0868 0.9987 0.0197
-12.000 -0.8040 0.03173 0.02717 -0.0916 0.9904 0.0202
-11.750 -0.7771 0.02981 0.02521 -0.0950 0.9848 0.0207
-11.500 -0.7482 0.02857 0.02391 -0.0980 0.9787 0.0213
-11.250 -0.7193 0.02713 0.02234 -0.1007 0.9732 0.0220
-11.000 -0.6890 0.02547 0.02048 -0.1034 0.9689 0.0227
-10.750 -0.6612 0.02401 0.01881 -0.1053 0.9611 0.0235
-10.500 -0.6296 0.02224 0.01684 -0.1078 0.9563 0.0243
-10.250 -0.6018 0.02121 0.01580 -0.1090 0.9467 0.0251
-10.000 -0.5706 0.02051 0.01503 -0.1108 0.9388 0.0261
-9.750 -0.5437 0.01980 0.01420 -0.1114 0.9283 0.0272
-9.500 -0.5185 0.01928 0.01351 -0.1115 0.9176 0.0282
-9.250 -0.4957 0.01808 0.01223 -0.1115 0.9082 0.0294
-9.000 -0.4736 0.01754 0.01166 -0.1110 0.8975 0.0304
-8.750 -0.4497 0.01704 0.01108 -0.1107 0.8886 0.0316
-8.500 -0.4261 0.01659 0.01052 -0.1103 0.8794 0.0330
-8.250 -0.4036 0.01586 0.00970 -0.1098 0.8710 0.0344
-8.000 -0.3804 0.01533 0.00916 -0.1095 0.8625 0.0360
-7.750 -0.3555 0.01493 0.00869 -0.1093 0.8549 0.0378
-7.500 -0.3304 0.01457 0.00825 -0.1090 0.8469 0.0394
-7.250 -0.3069 0.01385 0.00747 -0.1088 0.8398 0.0413
-7.000 -0.2816 0.01347 0.00708 -0.1087 0.8320 0.0436
-6.750 -0.2552 0.01316 0.00668 -0.1086 0.8254 0.0458
-6.500 -0.2296 0.01267 0.00614 -0.1086 0.8181 0.0481
-6.250 -0.2033 0.01225 0.00571 -0.1087 0.8112 0.0512
-6.000 -0.1761 0.01199 0.00538 -0.1088 0.8048 0.0543
-5.750 -0.1492 0.01155 0.00492 -0.1089 0.7978 0.0582
-5.500 -0.1214 0.01128 0.00459 -0.1091 0.7916 0.0632
-5.250 -0.0938 0.01091 0.00423 -0.1094 0.7849 0.0706
-5.000 -0.0658 0.01055 0.00390 -0.1097 0.7785 0.0853
-4.750 -0.0378 0.01001 0.00354 -0.1102 0.7725 0.1327
-4.500 -0.0096 0.00929 0.00318 -0.1111 0.7657 0.2230
-4.250 0.0193 0.00858 0.00288 -0.1122 0.7598 0.3409
-4.000 0.0486 0.00825 0.00277 -0.1128 0.7538 0.4163
-3.750 0.0778 0.00813 0.00271 -0.1131 0.7473 0.4541
-3.500 0.1070 0.00809 0.00266 -0.1134 0.7415 0.4806
-3.250 0.1361 0.00806 0.00263 -0.1137 0.7353 0.5007
-3.000 0.1653 0.00804 0.00260 -0.1139 0.7291 0.5162
-2.750 0.1944 0.00807 0.00257 -0.1141 0.7234 0.5306
-2.500 0.2234 0.00806 0.00259 -0.1143 0.7170 0.5479
-2.250 0.2524 0.00811 0.00261 -0.1145 0.7111 0.5651
-2.000 0.2815 0.00815 0.00262 -0.1147 0.7055 0.5767
-1.750 0.3105 0.00817 0.00263 -0.1149 0.6991 0.5873
-1.500 0.3393 0.00821 0.00265 -0.1150 0.6934 0.5976
-1.250 0.3684 0.00826 0.00266 -0.1152 0.6876 0.6062
-1.000 0.3972 0.00826 0.00267 -0.1154 0.6816 0.6131
-0.750 0.4261 0.00832 0.00267 -0.1156 0.6761 0.6205
-0.500 0.4551 0.00834 0.00269 -0.1158 0.6701 0.6275
-0.250 0.4838 0.00836 0.00272 -0.1160 0.6642 0.6341
0.000 0.5129 0.00845 0.00273 -0.1162 0.6589 0.6412
0.250 0.5414 0.00844 0.00278 -0.1164 0.6530 0.6474
0.500 0.5701 0.00849 0.00282 -0.1165 0.6471 0.6541
0.750 0.5991 0.00858 0.00286 -0.1168 0.6419 0.6608
1.000 0.6275 0.00859 0.00293 -0.1169 0.6360 0.6670
1.250 0.6562 0.00866 0.00298 -0.1171 0.6302 0.6741
1.500 0.6847 0.00874 0.00305 -0.1172 0.6248 0.6804
1.750 0.7130 0.00877 0.00314 -0.1173 0.6187 0.6871
2.000 0.7417 0.00886 0.00320 -0.1175 0.6130 0.6945
2.250 0.7698 0.00893 0.00331 -0.1176 0.6074 0.7007
2.500 0.7981 0.00899 0.00340 -0.1177 0.6012 0.7079
2.750 0.8262 0.00908 0.00348 -0.1178 0.5956 0.7146
3.000 0.8542 0.00916 0.00362 -0.1178 0.5898 0.7218
3.250 0.8823 0.00923 0.00372 -0.1179 0.5834 0.7293
3.500 0.9098 0.00935 0.00383 -0.1179 0.5770 0.7359
3.750 0.9374 0.00940 0.00395 -0.1179 0.5690 0.7438
4.250 0.9917 0.00958 0.00419 -0.1177 0.5535 0.7586
4.500 1.0183 0.00971 0.00432 -0.1175 0.5454 0.7657
4.750 1.0450 0.00977 0.00446 -0.1173 0.5356 0.7736
5.000 1.0710 0.00988 0.00459 -0.1170 0.5248 0.7814
5.250 1.0962 0.01002 0.00473 -0.1165 0.5119 0.7894
5.500 1.1212 0.01017 0.00488 -0.1160 0.4972 0.7975
5.750 1.1464 0.01030 0.00506 -0.1155 0.4838 0.8059
6.000 1.1714 0.01046 0.00526 -0.1151 0.4706 0.8144
6.250 1.1956 0.01066 0.00548 -0.1145 0.4555 0.8233
6.500 1.2187 0.01089 0.00572 -0.1137 0.4382 0.8322
6.750 1.2407 0.01121 0.00599 -0.1128 0.4177 0.8423
7.000 1.2607 0.01155 0.00631 -0.1114 0.3906 0.8519
7.250 1.2771 0.01211 0.00674 -0.1096 0.3540 0.8629
7.500 1.2893 0.01288 0.00730 -0.1071 0.3090 0.8756
8.000 1.3004 0.01468 0.00870 -0.0999 0.2184 0.9088
8.250 1.2959 0.01538 0.00929 -0.0942 0.1865 0.9461
8.500 1.3013 0.01640 0.01012 -0.0911 0.1502 1.0000
8.750 1.3074 0.01758 0.01110 -0.0885 0.1188 1.0000
9.000 1.3131 0.01880 0.01216 -0.0859 0.0937 1.0000
9.250 1.3188 0.02006 0.01331 -0.0835 0.0744 1.0000
9.500 1.3255 0.02133 0.01450 -0.0813 0.0610 1.0000
9.750 1.3336 0.02257 0.01570 -0.0794 0.0530 1.0000
10.000 1.3405 0.02394 0.01705 -0.0776 0.0476 1.0000
10.250 1.3511 0.02511 0.01827 -0.0762 0.0442 1.0000
10.500 1.3575 0.02663 0.01979 -0.0745 0.0412 1.0000
10.750 1.3667 0.02800 0.02122 -0.0732 0.0389 1.0000
11.000 1.3759 0.02941 0.02268 -0.0720 0.0368 1.0000
11.250 1.3806 0.03124 0.02453 -0.0706 0.0348 1.0000
11.500 1.3870 0.03298 0.02634 -0.0694 0.0331 1.0000
11.750 1.3958 0.03457 0.02799 -0.0685 0.0314 1.0000
12.000 1.4014 0.03648 0.02994 -0.0676 0.0298 1.0000
12.250 1.4003 0.03909 0.03260 -0.0664 0.0283 1.0000
12.500 1.4086 0.04088 0.03447 -0.0657 0.0272 1.0000
12.750 1.4147 0.04292 0.03658 -0.0651 0.0259 1.0000
13.000 1.4188 0.04523 0.03894 -0.0645 0.0249 1.0000
13.250 1.4159 0.04834 0.04209 -0.0639 0.0240 1.0000
13.500 1.4193 0.05090 0.04474 -0.0635 0.0232 1.0000
13.750 1.4248 0.05327 0.04722 -0.0632 0.0224 1.0000
14.000 1.4293 0.05583 0.04985 -0.0631 0.0217 1.0000
14.250 1.4329 0.05852 0.05260 -0.0630 0.0211 1.0000
14.500 1.4352 0.06144 0.05558 -0.0631 0.0205 1.0000
14.750 1.4341 0.06482 0.05901 -0.0632 0.0200 1.0000
15.000 1.4338 0.06816 0.06241 -0.0633 0.0195 1.0000
15.250 1.4386 0.07097 0.06534 -0.0636 0.0191 1.0000
15.500 1.4425 0.07393 0.06841 -0.0640 0.0186 1.0000
15.750 1.4460 0.07699 0.07156 -0.0644 0.0182 1.0000
16.000 1.4490 0.08017 0.07483 -0.0650 0.0178 1.0000
16.250 1.4518 0.08341 0.07814 -0.0657 0.0174 1.0000
16.500 1.4540 0.08675 0.08155 -0.0665 0.0171 1.0000
16.750 1.4557 0.09021 0.08507 -0.0673 0.0168 1.0000
17.000 1.4569 0.09368 0.08859 -0.0681 0.0165 1.0000
17.250 1.4580 0.09701 0.09197 -0.0685 0.0161 1.0000
17.500 1.4592 0.10071 0.09581 -0.0696 0.0160 1.0000
17.750 1.4600 0.10449 0.09972 -0.0709 0.0158 1.0000
18.000 1.4607 0.10830 0.10366 -0.0722 0.0156 1.0000
18.250 1.4605 0.11231 0.10779 -0.0737 0.0154 1.0000
18.500 1.4601 0.11636 0.11197 -0.0753 0.0152 1.0000
18.750 1.4593 0.12048 0.11622 -0.0770 0.0150 1.0000
19.000 1.4578 0.12480 0.12066 -0.0790 0.0149 1.0000
19.250 1.4557 0.12923 0.12521 -0.0811 0.0147 1.0000
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Polar data table (+)
Polar graphs
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