NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLR-7223-43 AIRFOIL (nl722343-il) Reynolds number: 50,000 Max Cl/Cd: 29.23 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nl722343-il-50000-n5.txt Download as CSV file: xf-nl722343-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NLR-7223-43 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4984 0.11200 0.10461 -0.0178 1.0000 0.1211
-9.500 -0.5261 0.11017 0.10299 -0.0236 1.0000 0.1283
-9.250 -0.5184 0.10565 0.09853 -0.0234 1.0000 0.1294
-9.000 -0.5018 0.09616 0.08889 -0.0271 1.0000 0.0656
-8.750 -0.5152 0.08960 0.08240 -0.0333 1.0000 0.0557
-8.500 -0.5145 0.08586 0.07871 -0.0333 1.0000 0.0540
-8.250 -0.5217 0.08200 0.07492 -0.0344 1.0000 0.0528
-8.000 -0.5294 0.07803 0.07098 -0.0354 1.0000 0.0514
-7.500 -0.5565 0.06866 0.06114 -0.0381 1.0000 0.0454
-7.250 -0.5537 0.06511 0.05751 -0.0374 1.0000 0.0451
-7.000 -0.5504 0.06162 0.05388 -0.0365 1.0000 0.0450
-6.750 -0.5455 0.05825 0.05033 -0.0356 1.0000 0.0448
-6.500 -0.5398 0.05485 0.04662 -0.0345 1.0000 0.0450
-6.250 -0.5309 0.05162 0.04310 -0.0334 1.0000 0.0449
-6.000 -0.5200 0.04846 0.03965 -0.0322 1.0000 0.0448
-5.750 -0.5071 0.04544 0.03635 -0.0310 1.0000 0.0444
-5.500 -0.4924 0.04254 0.03312 -0.0298 1.0000 0.0441
-5.250 -0.4758 0.03978 0.02999 -0.0285 1.0000 0.0439
-5.000 -0.4574 0.03724 0.02707 -0.0273 1.0000 0.0439
-4.750 -0.4374 0.03491 0.02435 -0.0260 1.0000 0.0441
-4.500 -0.4160 0.03289 0.02189 -0.0247 1.0000 0.0449
-4.250 -0.3948 0.03091 0.01970 -0.0237 1.0000 0.0469
-4.000 -0.3732 0.02935 0.01803 -0.0226 1.0000 0.0496
-3.750 -0.3504 0.02788 0.01638 -0.0212 1.0000 0.0517
-3.500 -0.3273 0.02659 0.01492 -0.0196 1.0000 0.0536
-3.250 -0.3049 0.02558 0.01365 -0.0179 1.0000 0.0568
-3.000 -0.2847 0.02447 0.01261 -0.0164 1.0000 0.0623
-2.750 -0.2638 0.02361 0.01160 -0.0148 1.0000 0.0683
-2.500 -0.2428 0.02266 0.01063 -0.0138 1.0000 0.0784
-2.250 -0.2214 0.02175 0.00968 -0.0128 1.0000 0.0963
-2.000 -0.1996 0.01977 0.00862 -0.0128 1.0000 0.2151
-1.750 -0.2097 0.01866 0.00974 -0.0028 1.0000 0.7686
-1.500 -0.1286 0.01917 0.01018 -0.0036 1.0000 0.9716
-1.250 -0.0939 0.01903 0.00975 -0.0057 1.0000 0.9802
-1.000 -0.0636 0.01891 0.00940 -0.0071 1.0000 0.9893
-0.750 -0.0367 0.01883 0.00914 -0.0081 1.0000 1.0000
-0.500 -0.0326 0.01865 0.00889 -0.0048 1.0000 1.0000
-0.250 -0.0278 0.01847 0.00866 -0.0018 1.0000 1.0000
0.000 -0.0198 0.01835 0.00846 0.0007 1.0000 1.0000
0.250 -0.0067 0.01831 0.00834 0.0023 1.0000 1.0000
0.500 0.0103 0.01836 0.00829 0.0032 1.0000 1.0000
0.750 0.0295 0.01848 0.00833 0.0037 1.0000 1.0000
1.000 0.0501 0.01865 0.00844 0.0040 1.0000 1.0000
1.250 0.1004 0.01921 0.00897 -0.0013 0.9863 1.0000
1.500 0.1572 0.01964 0.00939 -0.0075 0.9661 1.0000
1.750 0.2245 0.01975 0.00955 -0.0148 0.9362 1.0000
2.000 0.2841 0.01954 0.00944 -0.0201 0.9063 1.0000
2.250 0.3322 0.01926 0.00926 -0.0232 0.8797 1.0000
2.500 0.3738 0.01894 0.00908 -0.0250 0.8514 1.0000
2.750 0.4053 0.01865 0.00890 -0.0249 0.8166 1.0000
3.000 0.4346 0.01839 0.00873 -0.0243 0.7719 1.0000
3.250 0.4636 0.01814 0.00853 -0.0235 0.6996 1.0000
3.500 0.5178 0.01802 0.00775 -0.0256 0.5510 1.0000
3.750 0.5386 0.01888 0.00795 -0.0239 0.4499 1.0000
4.000 0.5586 0.01978 0.00844 -0.0226 0.3892 1.0000
4.250 0.5808 0.02065 0.00906 -0.0219 0.3504 1.0000
4.500 0.6051 0.02146 0.00971 -0.0216 0.3223 1.0000
4.750 0.6310 0.02225 0.01040 -0.0215 0.3011 1.0000
5.000 0.6583 0.02304 0.01117 -0.0216 0.2844 1.0000
5.250 0.6865 0.02383 0.01201 -0.0218 0.2696 1.0000
5.500 0.7150 0.02465 0.01285 -0.0221 0.2560 1.0000
5.750 0.7429 0.02550 0.01373 -0.0223 0.2435 1.0000
6.000 0.7701 0.02635 0.01475 -0.0223 0.2307 1.0000
6.250 0.7964 0.02726 0.01582 -0.0223 0.2182 1.0000
6.500 0.8220 0.02825 0.01695 -0.0221 0.2062 1.0000
6.750 0.8464 0.02926 0.01811 -0.0217 0.1936 1.0000
7.000 0.8695 0.03029 0.01926 -0.0212 0.1802 1.0000
7.250 0.8913 0.03134 0.02046 -0.0205 0.1661 1.0000
7.500 0.9111 0.03237 0.02170 -0.0196 0.1504 1.0000
7.750 0.9285 0.03330 0.02289 -0.0183 0.1330 1.0000
8.000 0.9452 0.03424 0.02401 -0.0170 0.1161 1.0000
8.250 0.9616 0.03524 0.02517 -0.0157 0.1011 1.0000
8.500 0.9775 0.03637 0.02640 -0.0144 0.0887 1.0000
8.750 0.9932 0.03797 0.02818 -0.0131 0.0784 1.0000
9.000 1.0079 0.04020 0.03069 -0.0117 0.0710 1.0000
9.250 1.0215 0.04199 0.03251 -0.0104 0.0660 1.0000
9.500 1.0315 0.04497 0.03593 -0.0089 0.0613 1.0000
9.750 1.0396 0.04753 0.03876 -0.0073 0.0576 1.0000
10.000 1.0480 0.04988 0.04121 -0.0059 0.0552 1.0000
10.250 1.0490 0.05338 0.04504 -0.0041 0.0539 1.0000
10.500 1.0396 0.05758 0.04972 -0.0020 0.0529 1.0000
10.750 1.0232 0.06169 0.05419 0.0002 0.0523 1.0000
11.000 1.0022 0.06629 0.05904 0.0013 0.0521 1.0000
11.250 0.9775 0.07176 0.06473 0.0007 0.0522 1.0000
11.500 0.9504 0.07848 0.07162 -0.0022 0.0527 1.0000
11.750 0.9216 0.08713 0.08037 -0.0078 0.0534 1.0000
12.000 0.8953 0.09740 0.09067 -0.0149 0.0541 1.0000
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Polar data table (+)
Polar graphs
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