NLR-7223-62 AIRFOIL (nl722362-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLR-7223-62 AIRFOIL (nl722362-il) Reynolds number: 500,000 Max Cl/Cd: 72.82 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nl722362-il-500000.txt Download as CSV file: xf-nl722362-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NLR-7223-62 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4978 0.08239 0.08012 -0.0357 1.0000 0.0162
-9.000 -0.5012 0.07816 0.07592 -0.0386 1.0000 0.0162
-8.750 -0.5197 0.07182 0.06956 -0.0434 1.0000 0.0162
-8.500 -0.5365 0.06997 0.06773 -0.0401 1.0000 0.0162
-8.250 -0.5491 0.06571 0.06336 -0.0399 0.9962 0.0162
-8.000 -0.5419 0.05979 0.05722 -0.0433 0.9906 0.0163
-7.500 -0.5216 0.05162 0.04893 -0.0472 0.9850 0.0170
-7.250 -0.5086 0.04871 0.04591 -0.0478 0.9806 0.0174
-7.000 -0.4919 0.04518 0.04220 -0.0488 0.9775 0.0181
-6.750 -0.4705 0.04052 0.03683 -0.0483 0.9745 0.0205
-6.500 -0.4616 0.03525 0.03139 -0.0478 0.9710 0.0211
-6.250 -0.4437 0.03359 0.02974 -0.0476 0.9680 0.0218
-6.000 -0.4242 0.03160 0.02758 -0.0471 0.9653 0.0230
-5.750 -0.3992 0.03121 0.02658 -0.0452 0.9627 0.0258
-5.500 -0.3832 0.02625 0.02152 -0.0449 0.9607 0.0271
-5.250 -0.3583 0.02527 0.02051 -0.0452 0.9594 0.0296
-5.000 -0.3374 0.02664 0.02146 -0.0424 0.9561 0.0324
-4.750 -0.3236 0.02210 0.01686 -0.0411 0.9534 0.0346
-4.500 -0.2975 0.01682 0.01079 -0.0381 0.9516 0.0194
-4.250 -0.2711 0.01524 0.00902 -0.0375 0.9504 0.0190
-4.000 -0.2445 0.01419 0.00785 -0.0371 0.9492 0.0191
-3.750 -0.2181 0.01350 0.00709 -0.0367 0.9481 0.0197
-3.500 -0.1912 0.01306 0.00659 -0.0365 0.9470 0.0204
-3.250 -0.1659 0.01227 0.00576 -0.0359 0.9458 0.0208
-3.000 -0.1419 0.01160 0.00508 -0.0352 0.9446 0.0217
-2.750 -0.1226 0.01131 0.00479 -0.0335 0.9421 0.0227
-2.500 -0.1010 0.01104 0.00450 -0.0320 0.9382 0.0247
-2.250 -0.0733 0.01057 0.00399 -0.0317 0.9337 0.0274
-2.000 -0.0441 0.01010 0.00354 -0.0315 0.9284 0.0403
-1.750 -0.0349 0.00860 0.00312 -0.0277 0.9183 0.3345
-1.500 -0.0284 0.00735 0.00289 -0.0231 0.9077 0.6185
-1.250 0.0431 0.00631 0.00280 -0.0312 0.8978 0.8889
-1.000 0.0896 0.00693 0.00341 -0.0340 0.8925 0.9438
-0.750 0.1341 0.00739 0.00380 -0.0368 0.8885 0.9624
-0.500 0.1796 0.00744 0.00377 -0.0403 0.8843 0.9662
-0.250 0.2156 0.00746 0.00376 -0.0419 0.8778 0.9718
0.000 0.2523 0.00745 0.00370 -0.0436 0.8712 0.9770
0.250 0.2930 0.00736 0.00358 -0.0463 0.8631 0.9814
0.500 0.3287 0.00730 0.00347 -0.0478 0.8543 0.9866
0.750 0.3668 0.00709 0.00324 -0.0500 0.8414 0.9899
1.000 0.4021 0.00695 0.00305 -0.0515 0.8243 0.9942
1.250 0.4386 0.00674 0.00281 -0.0533 0.7968 0.9976
1.500 0.4609 0.00694 0.00240 -0.0518 0.6469 1.0000
1.750 0.4735 0.00767 0.00250 -0.0489 0.5100 1.0000
2.000 0.4901 0.00827 0.00262 -0.0469 0.4025 1.0000
2.250 0.5087 0.00877 0.00273 -0.0454 0.3189 1.0000
2.500 0.5287 0.00919 0.00287 -0.0440 0.2593 1.0000
2.750 0.5500 0.00951 0.00301 -0.0429 0.2266 1.0000
3.000 0.5723 0.00974 0.00315 -0.0419 0.2089 1.0000
3.250 0.5945 0.00997 0.00331 -0.0409 0.1968 1.0000
3.500 0.6175 0.01014 0.00346 -0.0400 0.1890 1.0000
3.750 0.6397 0.01039 0.00365 -0.0389 0.1819 1.0000
4.000 0.6629 0.01052 0.00382 -0.0381 0.1773 1.0000
4.250 0.6856 0.01072 0.00401 -0.0371 0.1717 1.0000
4.500 0.7078 0.01098 0.00425 -0.0361 0.1665 1.0000
4.750 0.7311 0.01113 0.00444 -0.0352 0.1627 1.0000
5.000 0.7538 0.01131 0.00462 -0.0343 0.1567 1.0000
5.250 0.7765 0.01150 0.00482 -0.0333 0.1493 1.0000
5.500 0.7996 0.01164 0.00497 -0.0325 0.1425 1.0000
5.750 0.8219 0.01188 0.00521 -0.0315 0.1364 1.0000
6.000 0.8452 0.01199 0.00538 -0.0307 0.1297 1.0000
6.250 0.8677 0.01220 0.00558 -0.0297 0.1219 1.0000
6.500 0.8903 0.01238 0.00575 -0.0288 0.1117 1.0000
6.750 0.9132 0.01254 0.00592 -0.0279 0.0971 1.0000
7.000 0.9336 0.01295 0.00620 -0.0267 0.0743 1.0000
7.250 0.9515 0.01366 0.00675 -0.0250 0.0491 1.0000
7.500 0.9688 0.01446 0.00745 -0.0232 0.0331 1.0000
7.750 0.9873 0.01510 0.00813 -0.0215 0.0280 1.0000
8.000 1.0044 0.01588 0.00892 -0.0196 0.0249 1.0000
8.250 1.0231 0.01643 0.00955 -0.0180 0.0229 1.0000
8.500 1.0406 0.01706 0.01025 -0.0163 0.0213 1.0000
8.750 1.0551 0.01795 0.01120 -0.0140 0.0201 1.0000
9.000 1.0679 0.01895 0.01230 -0.0115 0.0193 1.0000
9.250 1.0834 0.01967 0.01311 -0.0093 0.0187 1.0000
9.500 1.0975 0.02048 0.01402 -0.0070 0.0181 1.0000
9.750 1.1108 0.02131 0.01494 -0.0047 0.0175 1.0000
10.000 1.1227 0.02222 0.01595 -0.0021 0.0170 1.0000
10.250 1.1338 0.02313 0.01693 0.0006 0.0166 1.0000
10.500 1.1430 0.02419 0.01807 0.0034 0.0163 1.0000
10.750 1.1491 0.02556 0.01952 0.0067 0.0159 1.0000
11.000 1.1536 0.02722 0.02130 0.0101 0.0156 1.0000
11.250 1.1543 0.02902 0.02325 0.0140 0.0153 1.0000
11.500 1.1560 0.02986 0.02424 0.0182 0.0151 1.0000
11.750 1.1577 0.03081 0.02534 0.0219 0.0148 1.0000
12.000 1.1581 0.03219 0.02687 0.0255 0.0147 1.0000
12.250 1.1577 0.03376 0.02860 0.0288 0.0146 1.0000
12.500 1.1550 0.03552 0.03054 0.0321 0.0144 1.0000
12.750 1.1512 0.03745 0.03264 0.0350 0.0143 1.0000
13.000 1.1459 0.03961 0.03498 0.0376 0.0143 1.0000
13.250 1.1367 0.04223 0.03780 0.0401 0.0143 1.0000
13.500 1.1263 0.04509 0.04084 0.0419 0.0142 1.0000
13.750 1.1137 0.04842 0.04436 0.0430 0.0143 1.0000
14.000 1.1010 0.05203 0.04815 0.0432 0.0142 1.0000
14.250 1.0823 0.05699 0.05332 0.0420 0.0142 1.0000
14.500 1.0667 0.06223 0.05873 0.0396 0.0141 1.0000
14.750 1.0467 0.06899 0.06568 0.0356 0.0142 1.0000
15.000 1.0242 0.07704 0.07391 0.0303 0.0144 1.0000
15.250 0.9997 0.08608 0.08311 0.0244 0.0145 1.0000
15.500 0.9728 0.09603 0.09320 0.0182 0.0146 1.0000
15.750 0.9466 0.10597 0.10325 0.0123 0.0148 1.0000
16.000 0.9085 0.11867 0.11604 0.0053 0.0152 1.0000
16.250 0.8724 0.13192 0.12939 -0.0018 0.0153 1.0000
16.500 0.7504 0.18016 0.17764 -0.0208 0.0254 1.0000
16.750 0.7595 0.18171 0.17921 -0.0206 0.0249 1.0000
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