NACA 747A415 (naca747a415-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 747A415 (naca747a415-il) Reynolds number: 500,000 Max Cl/Cd: 97.54 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca747a415-il-500000.txt Download as CSV file: xf-naca747a415-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 747A415
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4018 0.08636 0.08388 -0.0530 0.8724 0.0321
-10.750 -0.6396 0.04795 0.04458 -0.0657 0.8480 0.0250
-10.500 -0.6503 0.04597 0.04243 -0.0621 0.8332 0.0251
-10.250 -0.6560 0.04303 0.03929 -0.0591 0.8206 0.0240
-10.000 -0.6682 0.03938 0.03532 -0.0555 0.8092 0.0238
-9.750 -0.6782 0.03534 0.03083 -0.0517 0.7993 0.0237
-9.500 -0.6809 0.03152 0.02654 -0.0484 0.7896 0.0238
-9.250 -0.6745 0.02866 0.02323 -0.0458 0.7812 0.0240
-9.000 -0.6612 0.02686 0.02104 -0.0439 0.7725 0.0244
-8.750 -0.6466 0.02447 0.01828 -0.0424 0.7652 0.0248
-8.500 -0.6254 0.02318 0.01692 -0.0418 0.7573 0.0255
-8.000 -0.5800 0.02158 0.01510 -0.0406 0.7428 0.0267
-7.750 -0.5568 0.02049 0.01382 -0.0400 0.7359 0.0272
-7.500 -0.5326 0.01956 0.01272 -0.0394 0.7295 0.0279
-7.250 -0.5079 0.01872 0.01172 -0.0390 0.7226 0.0286
-7.000 -0.4832 0.01834 0.01115 -0.0384 0.7165 0.0292
-6.750 -0.4581 0.01691 0.00971 -0.0383 0.7102 0.0303
-6.500 -0.4331 0.01638 0.00914 -0.0379 0.7039 0.0312
-6.250 -0.4080 0.01588 0.00856 -0.0375 0.6981 0.0322
-6.000 -0.3826 0.01535 0.00798 -0.0371 0.6917 0.0333
-5.750 -0.3574 0.01491 0.00745 -0.0367 0.6858 0.0342
-5.500 -0.3337 0.01425 0.00673 -0.0361 0.6802 0.0356
-5.250 -0.3092 0.01379 0.00629 -0.0356 0.6743 0.0372
-5.000 -0.2842 0.01348 0.00593 -0.0352 0.6689 0.0390
-4.750 -0.2588 0.01318 0.00557 -0.0348 0.6638 0.0407
-4.500 -0.2353 0.01264 0.00502 -0.0341 0.6583 0.0431
-4.250 -0.2100 0.01236 0.00472 -0.0338 0.6532 0.0460
-4.000 -0.1843 0.01215 0.00444 -0.0334 0.6485 0.0495
-3.750 -0.1592 0.01179 0.00412 -0.0330 0.6434 0.0550
-3.500 -0.1339 0.01149 0.00381 -0.0327 0.6386 0.0621
-3.250 -0.1085 0.01124 0.00355 -0.0323 0.6343 0.0734
-3.000 -0.0834 0.01090 0.00333 -0.0319 0.6300 0.0984
-2.750 -0.0618 0.01023 0.00309 -0.0312 0.6256 0.1997
-2.500 -0.0446 0.00923 0.00282 -0.0299 0.6217 0.3905
-2.250 -0.0326 0.00801 0.00255 -0.0274 0.6180 0.6390
-2.000 -0.0108 0.00789 0.00283 -0.0257 0.6143 0.7644
-1.750 0.0162 0.00801 0.00297 -0.0253 0.6102 0.7914
-1.500 0.0433 0.00816 0.00309 -0.0249 0.6066 0.8087
-1.250 0.0706 0.00832 0.00318 -0.0246 0.6033 0.8211
-1.000 0.0978 0.00853 0.00333 -0.0242 0.6002 0.8318
-0.750 0.1242 0.00873 0.00357 -0.0235 0.5972 0.8427
-0.500 0.1486 0.00907 0.00393 -0.0221 0.5942 0.8573
-0.250 0.1719 0.00943 0.00430 -0.0203 0.5913 0.8712
0.000 0.1972 0.00967 0.00452 -0.0193 0.5887 0.8789
0.250 0.2248 0.00979 0.00455 -0.0194 0.5862 0.8842
0.500 0.2514 0.00984 0.00459 -0.0190 0.5838 0.8869
0.750 0.2786 0.00988 0.00464 -0.0188 0.5815 0.8896
1.000 0.3061 0.00992 0.00466 -0.0188 0.5789 0.8924
1.250 0.3343 0.00993 0.00465 -0.0190 0.5764 0.8947
1.500 0.3628 0.00994 0.00464 -0.0194 0.5742 0.8967
1.750 0.3915 0.00997 0.00463 -0.0199 0.5721 0.8987
2.000 0.4204 0.01003 0.00465 -0.0204 0.5702 0.9004
2.250 0.4482 0.01009 0.00470 -0.0205 0.5682 0.9019
2.500 0.4759 0.01009 0.00474 -0.0207 0.5663 0.9033
2.750 0.5038 0.01012 0.00479 -0.0208 0.5642 0.9048
3.000 0.5317 0.01016 0.00485 -0.0210 0.5620 0.9066
3.250 0.5599 0.01018 0.00488 -0.0213 0.5593 0.9082
3.500 0.5883 0.01021 0.00490 -0.0217 0.5566 0.9099
3.750 0.6169 0.01028 0.00496 -0.0221 0.5542 0.9116
4.000 0.6454 0.01040 0.00508 -0.0225 0.5518 0.9135
4.250 0.6737 0.01043 0.00517 -0.0230 0.5495 0.9153
4.500 0.7013 0.01045 0.00525 -0.0232 0.5468 0.9168
4.750 0.7285 0.01043 0.00526 -0.0232 0.5431 0.9183
5.000 0.7560 0.01044 0.00525 -0.0233 0.5385 0.9199
5.250 0.7827 0.01047 0.00533 -0.0233 0.5339 0.9217
5.500 0.8091 0.01042 0.00534 -0.0232 0.5280 0.9237
5.750 0.8357 0.01041 0.00528 -0.0231 0.5201 0.9260
6.000 0.8611 0.01032 0.00529 -0.0229 0.5119 0.9286
6.500 0.9127 0.01031 0.00536 -0.0226 0.4975 0.9328
6.750 0.9373 0.01034 0.00539 -0.0221 0.4890 0.9351
7.000 0.9613 0.01031 0.00546 -0.0216 0.4781 0.9379
7.250 0.9852 0.01035 0.00555 -0.0212 0.4659 0.9409
7.500 1.0083 0.01042 0.00565 -0.0206 0.4491 0.9441
7.750 1.0281 0.01054 0.00575 -0.0194 0.4203 0.9476
8.000 1.0336 0.01116 0.00608 -0.0159 0.3570 0.9544
8.250 1.0319 0.01222 0.00682 -0.0116 0.2956 0.9634
8.500 1.0317 0.01347 0.00779 -0.0082 0.2367 0.9748
8.750 1.0432 0.01522 0.00925 -0.0084 0.1763 0.9864
9.000 1.0471 0.01691 0.01068 -0.0075 0.1313 1.0000
9.250 1.0429 0.01854 0.01213 -0.0048 0.0989 1.0000
9.500 1.0421 0.02026 0.01370 -0.0028 0.0736 1.0000
9.750 1.0420 0.02207 0.01538 -0.0011 0.0536 1.0000
10.000 1.0452 0.02374 0.01699 0.0003 0.0433 1.0000
10.250 1.0507 0.02532 0.01857 0.0015 0.0383 1.0000
10.500 1.0555 0.02696 0.02020 0.0026 0.0346 1.0000
10.750 1.0619 0.02854 0.02183 0.0036 0.0324 1.0000
11.000 1.0688 0.03010 0.02341 0.0044 0.0301 1.0000
11.250 1.0696 0.03218 0.02552 0.0055 0.0283 1.0000
11.500 1.0757 0.03387 0.02727 0.0063 0.0274 1.0000
11.750 1.0831 0.03548 0.02894 0.0070 0.0262 1.0000
12.000 1.0882 0.03732 0.03082 0.0076 0.0250 1.0000
12.250 1.0919 0.03934 0.03287 0.0083 0.0242 1.0000
12.500 1.0898 0.04190 0.03547 0.0091 0.0231 1.0000
12.750 1.0968 0.04371 0.03734 0.0095 0.0228 1.0000
13.000 1.1048 0.04547 0.03917 0.0098 0.0221 1.0000
13.250 1.1114 0.04738 0.04113 0.0101 0.0212 1.0000
13.500 1.1176 0.04935 0.04315 0.0104 0.0208 1.0000
13.750 1.1239 0.05133 0.04516 0.0106 0.0202 1.0000
14.000 1.1295 0.05340 0.04725 0.0108 0.0197 1.0000
14.250 1.1313 0.05567 0.04954 0.0115 0.0191 1.0000
14.500 1.1406 0.05751 0.05147 0.0114 0.0188 1.0000
14.750 1.1487 0.05941 0.05345 0.0115 0.0185 1.0000
15.000 1.1568 0.06131 0.05542 0.0116 0.0183 1.0000
15.250 1.1648 0.06324 0.05742 0.0117 0.0179 1.0000
15.500 1.1725 0.06528 0.05953 0.0116 0.0174 1.0000
15.750 1.1808 0.06722 0.06153 0.0116 0.0173 1.0000
16.000 1.1876 0.06942 0.06380 0.0114 0.0170 1.0000
16.250 1.1951 0.07148 0.06593 0.0113 0.0167 1.0000
16.500 1.2019 0.07370 0.06820 0.0110 0.0165 1.0000
16.750 1.2096 0.07579 0.07035 0.0109 0.0163 1.0000
17.000 1.2172 0.07789 0.07250 0.0107 0.0161 1.0000
17.250 1.2279 0.07954 0.07420 0.0112 0.0158 1.0000
17.500 1.2332 0.08208 0.07687 0.0112 0.0156 1.0000
17.750 1.2287 0.08610 0.08106 0.0096 0.0154 1.0000
18.000 1.2279 0.08966 0.08478 0.0087 0.0154 1.0000
18.250 1.2248 0.09364 0.08892 0.0074 0.0152 1.0000
18.500 1.2213 0.09772 0.09315 0.0058 0.0151 1.0000
18.750 1.2149 0.10236 0.09797 0.0041 0.0150 1.0000
19.000 1.2079 0.10721 0.10299 0.0020 0.0149 1.0000
19.250 1.1991 0.11247 0.10842 -0.0003 0.0149 1.0000
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