NACA 747A415 (naca747a415-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 747A415 (naca747a415-il) Reynolds number: 200,000 Max Cl/Cd: 66.42 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca747a415-il-200000-n5.txt Download as CSV file: xf-naca747a415-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4476 0.09886 0.09536 -0.0411 0.9617 0.0236
-11.750 -0.5292 0.06937 0.06578 -0.0621 0.9441 0.0227
-11.500 -0.5659 0.05933 0.05543 -0.0702 0.9130 0.0226
-11.250 -0.5941 0.05407 0.04989 -0.0710 0.8887 0.0225
-11.000 -0.6235 0.04957 0.04506 -0.0693 0.8688 0.0225
-10.750 -0.6523 0.04556 0.04069 -0.0655 0.8510 0.0226
-10.500 -0.6734 0.04236 0.03709 -0.0610 0.8366 0.0227
-10.250 -0.6878 0.03869 0.03288 -0.0570 0.8240 0.0230
-10.000 -0.6810 0.03690 0.03088 -0.0551 0.8133 0.0232
-9.750 -0.6706 0.03551 0.02931 -0.0533 0.8035 0.0236
-9.500 -0.6573 0.03436 0.02800 -0.0518 0.7933 0.0240
-9.250 -0.6437 0.03305 0.02647 -0.0503 0.7845 0.0246
-9.000 -0.6297 0.03150 0.02463 -0.0488 0.7755 0.0254
-8.750 -0.6151 0.02965 0.02240 -0.0472 0.7678 0.0261
-8.500 -0.5980 0.02774 0.02008 -0.0458 0.7599 0.0268
-8.000 -0.5564 0.02505 0.01690 -0.0441 0.7458 0.0279
-7.750 -0.5340 0.02427 0.01602 -0.0435 0.7389 0.0286
-7.500 -0.5109 0.02352 0.01514 -0.0430 0.7324 0.0296
-7.250 -0.4871 0.02267 0.01412 -0.0424 0.7254 0.0307
-7.000 -0.4629 0.02178 0.01301 -0.0419 0.7194 0.0316
-6.750 -0.4378 0.02094 0.01200 -0.0415 0.7127 0.0324
-6.500 -0.4138 0.02011 0.01116 -0.0410 0.7064 0.0333
-6.250 -0.3898 0.01952 0.01050 -0.0405 0.7010 0.0343
-6.000 -0.3652 0.01899 0.00993 -0.0401 0.6947 0.0360
-5.750 -0.3407 0.01847 0.00930 -0.0396 0.6891 0.0377
-5.500 -0.3173 0.01789 0.00865 -0.0390 0.6843 0.0393
-5.250 -0.2934 0.01739 0.00816 -0.0385 0.6784 0.0409
-5.000 -0.2695 0.01695 0.00767 -0.0379 0.6731 0.0430
-4.750 -0.2454 0.01658 0.00720 -0.0373 0.6686 0.0458
-4.500 -0.2217 0.01615 0.00679 -0.0368 0.6634 0.0492
-4.250 -0.1972 0.01582 0.00640 -0.0363 0.6583 0.0532
-4.000 -0.1734 0.01545 0.00601 -0.0357 0.6539 0.0581
-3.750 -0.1488 0.01516 0.00566 -0.0352 0.6496 0.0652
-3.500 -0.1241 0.01484 0.00537 -0.0348 0.6445 0.0750
-3.250 -0.1001 0.01449 0.00508 -0.0343 0.6399 0.0923
-3.000 -0.0770 0.01407 0.00480 -0.0336 0.6360 0.1323
-2.750 -0.0566 0.01340 0.00455 -0.0328 0.6320 0.2292
-2.500 -0.0407 0.01245 0.00429 -0.0312 0.6279 0.3926
-2.250 -0.0289 0.01142 0.00418 -0.0283 0.6242 0.6013
-2.000 -0.0073 0.01155 0.00480 -0.0258 0.6209 0.7494
-1.750 0.0178 0.01175 0.00491 -0.0248 0.6180 0.7839
-1.500 0.0429 0.01199 0.00513 -0.0239 0.6142 0.8081
-1.250 0.0652 0.01247 0.00561 -0.0218 0.6107 0.8379
-1.000 0.0898 0.01304 0.00618 -0.0197 0.6075 0.8589
-0.750 0.1165 0.01328 0.00634 -0.0189 0.6047 0.8687
-0.500 0.1426 0.01336 0.00632 -0.0184 0.6021 0.8748
-0.250 0.1714 0.01348 0.00640 -0.0184 0.5991 0.8793
0.000 0.1978 0.01351 0.00639 -0.0182 0.5957 0.8837
0.250 0.2224 0.01349 0.00631 -0.0178 0.5925 0.8875
0.500 0.2486 0.01348 0.00624 -0.0177 0.5899 0.8901
0.750 0.2770 0.01350 0.00621 -0.0179 0.5876 0.8917
1.000 0.3051 0.01353 0.00618 -0.0181 0.5855 0.8936
1.250 0.3323 0.01357 0.00620 -0.0182 0.5831 0.8957
1.500 0.3589 0.01361 0.00625 -0.0182 0.5805 0.8982
1.750 0.3850 0.01365 0.00629 -0.0182 0.5781 0.9008
2.000 0.4107 0.01368 0.00631 -0.0180 0.5756 0.9034
2.250 0.4369 0.01371 0.00633 -0.0180 0.5732 0.9059
2.500 0.4649 0.01376 0.00637 -0.0182 0.5711 0.9074
2.750 0.4931 0.01383 0.00641 -0.0185 0.5693 0.9089
3.000 0.5204 0.01392 0.00654 -0.0187 0.5674 0.9107
3.250 0.5468 0.01402 0.00669 -0.0187 0.5649 0.9131
3.500 0.5728 0.01411 0.00683 -0.0187 0.5622 0.9156
3.750 0.5988 0.01419 0.00695 -0.0186 0.5596 0.9179
4.000 0.6248 0.01426 0.00704 -0.0186 0.5569 0.9203
4.250 0.6524 0.01432 0.00711 -0.0188 0.5543 0.9220
4.500 0.6806 0.01441 0.00723 -0.0191 0.5518 0.9236
4.750 0.7062 0.01454 0.00748 -0.0190 0.5485 0.9260
5.000 0.7321 0.01466 0.00768 -0.0189 0.5451 0.9287
5.250 0.7582 0.01476 0.00785 -0.0189 0.5419 0.9313
5.500 0.7847 0.01483 0.00795 -0.0189 0.5388 0.9339
5.750 0.8104 0.01488 0.00806 -0.0188 0.5340 0.9364
6.000 0.8358 0.01492 0.00823 -0.0186 0.5271 0.9387
6.250 0.8639 0.01489 0.00820 -0.0188 0.5211 0.9409
6.500 0.8871 0.01493 0.00837 -0.0183 0.5119 0.9442
6.750 0.9105 0.01484 0.00832 -0.0176 0.5001 0.9479
7.000 0.9346 0.01480 0.00831 -0.0172 0.4865 0.9515
7.250 0.9593 0.01484 0.00842 -0.0170 0.4713 0.9550
7.500 0.9811 0.01494 0.00863 -0.0163 0.4517 0.9597
7.750 1.0029 0.01510 0.00883 -0.0158 0.4227 0.9642
8.000 1.0192 0.01557 0.00905 -0.0147 0.3647 0.9703
8.250 1.0255 0.01682 0.00995 -0.0129 0.3026 0.9802
8.500 1.0260 0.01835 0.01122 -0.0109 0.2502 1.0000
8.750 1.0136 0.01959 0.01230 -0.0062 0.2212 1.0000
9.000 1.0068 0.02123 0.01377 -0.0031 0.1889 1.0000
9.250 1.0024 0.02306 0.01543 -0.0008 0.1579 1.0000
9.500 0.9997 0.02497 0.01719 0.0011 0.1299 1.0000
9.750 0.9975 0.02699 0.01906 0.0027 0.1045 1.0000
10.000 0.9963 0.02905 0.02099 0.0042 0.0835 1.0000
10.250 0.9978 0.03096 0.02283 0.0053 0.0673 1.0000
10.500 1.0011 0.03281 0.02463 0.0063 0.0558 1.0000
10.750 1.0049 0.03465 0.02643 0.0071 0.0475 1.0000
11.000 1.0100 0.03643 0.02822 0.0079 0.0421 1.0000
11.250 1.0142 0.03833 0.03012 0.0086 0.0383 1.0000
11.500 1.0207 0.04007 0.03191 0.0092 0.0356 1.0000
11.750 1.0244 0.04211 0.03398 0.0097 0.0330 1.0000
12.000 1.0303 0.04401 0.03595 0.0101 0.0315 1.0000
12.250 1.0363 0.04595 0.03796 0.0105 0.0299 1.0000
12.500 1.0413 0.04802 0.04009 0.0108 0.0285 1.0000
12.750 1.0442 0.05035 0.04244 0.0110 0.0273 1.0000
13.000 1.0502 0.05241 0.04459 0.0112 0.0260 1.0000
13.250 1.0556 0.05457 0.04683 0.0113 0.0251 1.0000
13.500 1.0612 0.05674 0.04907 0.0114 0.0242 1.0000
13.750 1.0664 0.05899 0.05137 0.0113 0.0232 1.0000
14.000 1.0698 0.06146 0.05387 0.0112 0.0226 1.0000
14.250 1.0751 0.06375 0.05623 0.0112 0.0220 1.0000
14.500 1.0815 0.06596 0.05855 0.0111 0.0215 1.0000
14.750 1.0878 0.06820 0.06088 0.0110 0.0209 1.0000
15.000 1.0940 0.07047 0.06323 0.0109 0.0204 1.0000
15.250 1.0998 0.07282 0.06565 0.0106 0.0198 1.0000
15.500 1.1059 0.07514 0.06804 0.0104 0.0195 1.0000
15.750 1.1118 0.07753 0.07048 0.0101 0.0191 1.0000
16.000 1.1179 0.07988 0.07289 0.0098 0.0188 1.0000
16.250 1.1244 0.08217 0.07520 0.0095 0.0184 1.0000
16.500 1.1304 0.08465 0.07783 0.0092 0.0182 1.0000
16.750 1.1357 0.08726 0.08058 0.0087 0.0180 1.0000
17.000 1.1396 0.09015 0.08361 0.0080 0.0177 1.0000
17.250 1.1427 0.09317 0.08679 0.0073 0.0174 1.0000
17.500 1.1436 0.09659 0.09037 0.0062 0.0171 1.0000
17.750 1.1436 0.10020 0.09414 0.0050 0.0168 1.0000
18.000 1.1428 0.10397 0.09806 0.0036 0.0166 1.0000
18.250 1.1412 0.10797 0.10221 0.0019 0.0164 1.0000
18.500 1.1384 0.11222 0.10660 0.0000 0.0161 1.0000
18.750 1.1343 0.11674 0.11127 -0.0021 0.0160 1.0000
19.000 1.1296 0.12148 0.11616 -0.0044 0.0158 1.0000
19.250 1.1246 0.12636 0.12118 -0.0070 0.0157 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 747A415 (naca747a415-il)