NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLR-7223-43 AIRFOIL (nl722343-il) Reynolds number: 200,000 Max Cl/Cd: 53.05 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nl722343-il-200000-n5.txt Download as CSV file: xf-nl722343-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4996 0.08700 0.08332 -0.0285 1.0000 0.0245
-8.750 -0.5039 0.08261 0.07899 -0.0307 1.0000 0.0247
-8.500 -0.5125 0.07769 0.07412 -0.0339 1.0000 0.0246
-8.250 -0.5284 0.07309 0.06956 -0.0365 1.0000 0.0245
-8.000 -0.5639 0.06255 0.05875 -0.0401 1.0000 0.0179
-7.750 -0.5604 0.06136 0.05761 -0.0384 1.0000 0.0172
-7.500 -0.5643 0.05829 0.05448 -0.0371 1.0000 0.0167
-7.000 -0.5803 0.04585 0.04135 -0.0329 1.0000 0.0139
-6.750 -0.5760 0.04313 0.03847 -0.0310 1.0000 0.0138
-6.500 -0.5668 0.03925 0.03427 -0.0298 0.9992 0.0138
-6.250 -0.5427 0.03647 0.03127 -0.0316 0.9962 0.0145
-6.000 -0.5171 0.03462 0.02924 -0.0329 0.9934 0.0156
-5.750 -0.4920 0.03113 0.02531 -0.0335 0.9902 0.0159
-5.500 -0.4652 0.02759 0.02127 -0.0340 0.9874 0.0156
-5.250 -0.4366 0.02467 0.01788 -0.0344 0.9854 0.0155
-5.000 -0.4102 0.02252 0.01536 -0.0342 0.9826 0.0156
-4.750 -0.3828 0.02078 0.01331 -0.0342 0.9799 0.0158
-4.500 -0.3542 0.01936 0.01164 -0.0343 0.9776 0.0162
-4.250 -0.3245 0.01813 0.01023 -0.0346 0.9755 0.0168
-4.000 -0.2937 0.01718 0.00913 -0.0353 0.9737 0.0181
-3.750 -0.2679 0.01646 0.00844 -0.0352 0.9704 0.0194
-3.500 -0.2411 0.01575 0.00769 -0.0351 0.9673 0.0204
-3.250 -0.2128 0.01506 0.00695 -0.0353 0.9647 0.0215
-3.000 -0.1828 0.01446 0.00630 -0.0359 0.9625 0.0227
-2.750 -0.1515 0.01391 0.00574 -0.0369 0.9606 0.0248
-2.500 -0.1250 0.01353 0.00533 -0.0368 0.9565 0.0295
-2.250 -0.0957 0.01312 0.00492 -0.0372 0.9525 0.0374
-2.000 -0.0641 0.01253 0.00453 -0.0382 0.9494 0.0837
-1.750 -0.0433 0.01045 0.00471 -0.0379 0.9465 0.6201
-1.500 -0.0187 0.01081 0.00506 -0.0366 0.9404 0.7171
-1.250 0.0101 0.01099 0.00534 -0.0356 0.9354 0.7623
-1.000 0.0476 0.01082 0.00516 -0.0368 0.9284 0.7794
-0.750 0.0911 0.01046 0.00469 -0.0392 0.9142 0.7822
-0.500 0.1282 0.01016 0.00428 -0.0404 0.8932 0.7834
-0.250 0.1609 0.01001 0.00404 -0.0411 0.8774 0.7843
0.000 0.1916 0.00993 0.00389 -0.0415 0.8655 0.7851
0.250 0.2214 0.00985 0.00376 -0.0417 0.8524 0.7862
0.500 0.2504 0.00979 0.00365 -0.0418 0.8370 0.7870
0.750 0.2792 0.00974 0.00355 -0.0418 0.8185 0.7877
1.000 0.3088 0.00970 0.00343 -0.0419 0.7951 0.7884
1.250 0.3370 0.00969 0.00333 -0.0417 0.7595 0.7894
1.500 0.3639 0.00982 0.00312 -0.0410 0.6710 0.7905
1.750 0.3846 0.01033 0.00307 -0.0392 0.5651 0.7914
2.000 0.4047 0.01087 0.00319 -0.0377 0.4742 0.7922
2.250 0.4260 0.01137 0.00334 -0.0365 0.3988 0.7930
2.500 0.4484 0.01182 0.00350 -0.0356 0.3363 0.7939
2.750 0.4719 0.01222 0.00367 -0.0350 0.2888 0.7948
3.000 0.4964 0.01255 0.00387 -0.0345 0.2565 0.7958
3.250 0.5214 0.01284 0.00407 -0.0341 0.2349 0.7968
3.500 0.5466 0.01311 0.00429 -0.0337 0.2195 0.7980
3.750 0.5719 0.01339 0.00452 -0.0333 0.2075 0.7994
4.000 0.5971 0.01369 0.00480 -0.0329 0.1976 0.8010
4.250 0.6228 0.01394 0.00506 -0.0326 0.1887 0.8026
4.500 0.6481 0.01426 0.00535 -0.0322 0.1816 0.8041
4.750 0.6739 0.01451 0.00565 -0.0319 0.1749 0.8056
5.000 0.6988 0.01485 0.00599 -0.0315 0.1688 0.8072
5.250 0.7242 0.01510 0.00633 -0.0311 0.1630 0.8088
5.500 0.7492 0.01539 0.00667 -0.0307 0.1568 0.8106
5.750 0.7740 0.01572 0.00706 -0.0303 0.1511 0.8126
6.000 0.7994 0.01596 0.00741 -0.0299 0.1434 0.8149
6.250 0.8245 0.01621 0.00771 -0.0295 0.1330 0.8175
6.500 0.8499 0.01645 0.00799 -0.0293 0.1206 0.8203
6.750 0.8751 0.01671 0.00832 -0.0289 0.1090 0.8234
7.000 0.9003 0.01697 0.00866 -0.0286 0.0930 0.8272
7.250 0.9239 0.01744 0.00906 -0.0281 0.0740 0.8318
7.750 0.9679 0.01890 0.01051 -0.0266 0.0430 0.8449
8.000 0.9890 0.01970 0.01138 -0.0256 0.0344 0.8555
8.250 1.0095 0.02050 0.01232 -0.0246 0.0297 0.8760
8.500 1.0360 0.02129 0.01336 -0.0248 0.0266 1.0000
8.750 1.0561 0.02224 0.01438 -0.0239 0.0243 1.0000
9.000 1.0749 0.02326 0.01550 -0.0228 0.0225 1.0000
9.250 1.0937 0.02423 0.01663 -0.0217 0.0212 1.0000
9.500 1.1111 0.02530 0.01782 -0.0204 0.0202 1.0000
9.750 1.1269 0.02647 0.01908 -0.0190 0.0194 1.0000
10.000 1.1399 0.02789 0.02059 -0.0173 0.0187 1.0000
10.250 1.1527 0.02933 0.02215 -0.0155 0.0182 1.0000
10.500 1.1655 0.03074 0.02375 -0.0137 0.0178 1.0000
10.750 1.1767 0.03226 0.02546 -0.0119 0.0173 1.0000
11.000 1.1853 0.03376 0.02715 -0.0097 0.0167 1.0000
11.250 1.1915 0.03532 0.02888 -0.0073 0.0163 1.0000
11.500 1.1963 0.03685 0.03055 -0.0049 0.0157 1.0000
11.750 1.1987 0.03862 0.03246 -0.0026 0.0154 1.0000
12.000 1.1997 0.04050 0.03448 -0.0005 0.0151 1.0000
12.250 1.1985 0.04266 0.03677 0.0014 0.0148 1.0000
12.500 1.1951 0.04517 0.03944 0.0030 0.0147 1.0000
12.750 1.1897 0.04803 0.04248 0.0042 0.0146 1.0000
13.000 1.1806 0.05153 0.04614 0.0049 0.0144 1.0000
13.250 1.1702 0.05534 0.05017 0.0047 0.0143 1.0000
13.500 1.1578 0.05983 0.05488 0.0034 0.0143 1.0000
13.750 1.1437 0.06517 0.06044 0.0009 0.0143 1.0000
14.000 1.1280 0.07150 0.06696 -0.0029 0.0143 1.0000
14.250 1.1099 0.07910 0.07477 -0.0081 0.0143 1.0000
14.500 1.0903 0.08762 0.08347 -0.0140 0.0143 1.0000
14.750 1.0716 0.09622 0.09221 -0.0197 0.0144 1.0000
15.000 1.0481 0.10640 0.10258 -0.0264 0.0145 1.0000
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Polar data table (+)
Polar graphs
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