NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLR-7223-43 AIRFOIL (nl722343-il) Reynolds number: 500,000 Max Cl/Cd: 70.16 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nl722343-il-500000.txt Download as CSV file: xf-nl722343-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5041 0.08351 0.08118 -0.0296 1.0000 0.0172
-8.750 -0.5128 0.07713 0.07484 -0.0349 1.0000 0.0175
-8.500 -0.5276 0.07192 0.06964 -0.0385 1.0000 0.0175
-8.250 -0.5439 0.06855 0.06626 -0.0385 1.0000 0.0174
-8.000 -0.5568 0.06373 0.06132 -0.0390 1.0000 0.0176
-7.750 -0.5671 0.05994 0.05740 -0.0375 1.0000 0.0177
-7.500 -0.5759 0.05682 0.05414 -0.0348 1.0000 0.0178
-7.250 -0.5828 0.05398 0.05114 -0.0318 1.0000 0.0178
-7.000 -0.5892 0.04892 0.04601 -0.0305 0.9996 0.0181
-6.750 -0.5678 0.04560 0.04260 -0.0331 0.9973 0.0184
-6.500 -0.5438 0.04258 0.03946 -0.0355 0.9952 0.0189
-6.250 -0.5198 0.03947 0.03617 -0.0372 0.9925 0.0197
-6.000 -0.4876 0.03657 0.03260 -0.0380 0.9892 0.0225
-5.750 -0.4660 0.03081 0.02661 -0.0400 0.9869 0.0233
-5.500 -0.4372 0.02889 0.02465 -0.0417 0.9855 0.0244
-5.250 -0.4109 0.02711 0.02262 -0.0418 0.9822 0.0271
-5.000 -0.3842 0.02418 0.01927 -0.0422 0.9791 0.0299
-4.750 -0.3545 0.02266 0.01768 -0.0433 0.9771 0.0316
-4.500 -0.3227 0.02121 0.01585 -0.0442 0.9753 0.0375
-4.250 -0.2908 0.01610 0.01020 -0.0428 0.9746 0.0202
-4.000 -0.2590 0.01418 0.00798 -0.0430 0.9738 0.0184
-3.750 -0.2338 0.01324 0.00700 -0.0425 0.9705 0.0186
-3.500 -0.2066 0.01250 0.00625 -0.0424 0.9675 0.0191
-3.250 -0.1766 0.01191 0.00565 -0.0430 0.9653 0.0201
-3.000 -0.1442 0.01139 0.00511 -0.0440 0.9634 0.0213
-2.750 -0.1066 0.01079 0.00449 -0.0461 0.9616 0.0234
-2.500 -0.0660 0.01020 0.00391 -0.0488 0.9602 0.0266
-2.250 -0.0346 0.00967 0.00337 -0.0493 0.9531 0.0331
-2.000 0.0013 0.00756 0.00259 -0.0520 0.9481 0.3979
-1.750 0.0296 0.00678 0.00263 -0.0517 0.9374 0.6786
-1.500 0.0625 0.00680 0.00261 -0.0520 0.9265 0.7051
-1.250 0.0912 0.00700 0.00283 -0.0514 0.9186 0.7328
-1.000 0.1164 0.00712 0.00304 -0.0501 0.9115 0.7550
-0.750 0.1429 0.00716 0.00311 -0.0493 0.9044 0.7699
-0.500 0.1710 0.00716 0.00306 -0.0491 0.8966 0.7748
-0.250 0.1991 0.00713 0.00297 -0.0489 0.8880 0.7782
0.000 0.2259 0.00706 0.00288 -0.0485 0.8780 0.7804
0.250 0.2539 0.00701 0.00279 -0.0483 0.8676 0.7816
0.500 0.2817 0.00697 0.00270 -0.0481 0.8551 0.7820
0.750 0.3087 0.00693 0.00262 -0.0478 0.8395 0.7824
1.000 0.3354 0.00691 0.00255 -0.0474 0.8199 0.7831
1.250 0.3620 0.00692 0.00247 -0.0469 0.7933 0.7835
1.500 0.3870 0.00700 0.00239 -0.0460 0.7447 0.7839
1.750 0.4040 0.00755 0.00234 -0.0435 0.6100 0.7843
2.000 0.4223 0.00820 0.00249 -0.0417 0.4934 0.7848
2.250 0.4430 0.00878 0.00263 -0.0405 0.3944 0.7853
2.500 0.4654 0.00930 0.00279 -0.0396 0.3130 0.7861
2.750 0.4892 0.00973 0.00294 -0.0390 0.2556 0.7867
3.000 0.5143 0.01005 0.00311 -0.0386 0.2241 0.7871
3.250 0.5400 0.01030 0.00326 -0.0383 0.2067 0.7876
3.500 0.5660 0.01053 0.00343 -0.0380 0.1952 0.7881
3.750 0.5921 0.01073 0.00360 -0.0378 0.1873 0.7886
4.000 0.6181 0.01096 0.00381 -0.0375 0.1807 0.7892
4.250 0.6446 0.01112 0.00399 -0.0373 0.1752 0.7898
4.500 0.6702 0.01139 0.00422 -0.0369 0.1695 0.7905
4.750 0.6965 0.01158 0.00445 -0.0367 0.1652 0.7911
5.000 0.7230 0.01174 0.00463 -0.0365 0.1597 0.7918
5.250 0.7482 0.01201 0.00488 -0.0361 0.1525 0.7926
5.500 0.7752 0.01206 0.00499 -0.0360 0.1458 0.7935
5.750 0.8003 0.01232 0.00524 -0.0356 0.1381 0.7947
6.000 0.8271 0.01239 0.00540 -0.0355 0.1320 0.7959
6.250 0.8524 0.01264 0.00563 -0.0351 0.1239 0.7971
6.500 0.8791 0.01273 0.00578 -0.0350 0.1145 0.7983
6.750 0.9051 0.01290 0.00596 -0.0347 0.1010 0.7997
7.000 0.9295 0.01327 0.00621 -0.0343 0.0785 0.8011
7.250 0.9515 0.01398 0.00678 -0.0335 0.0509 0.8027
7.500 0.9728 0.01484 0.00753 -0.0326 0.0332 0.8044
7.750 0.9951 0.01554 0.00826 -0.0317 0.0277 0.8062
8.000 1.0174 0.01619 0.00896 -0.0309 0.0249 0.8083
8.250 1.0379 0.01703 0.00991 -0.0297 0.0229 0.8107
8.500 1.0597 0.01767 0.01067 -0.0288 0.0215 0.8136
8.750 1.0806 0.01837 0.01146 -0.0278 0.0203 0.8170
9.000 1.0987 0.01938 0.01255 -0.0264 0.0191 0.8209
9.250 1.1150 0.02055 0.01387 -0.0248 0.0182 0.8262
9.500 1.1340 0.02135 0.01482 -0.0235 0.0177 0.8336
9.750 1.1513 0.02224 0.01590 -0.0219 0.0173 0.8456
10.000 1.1659 0.02302 0.01696 -0.0198 0.0167 0.8876
10.250 1.1896 0.02424 0.01838 -0.0199 0.0163 1.0000
10.500 1.2054 0.02543 0.01968 -0.0184 0.0158 1.0000
10.750 1.2196 0.02676 0.02112 -0.0168 0.0155 1.0000
11.000 1.2323 0.02819 0.02264 -0.0150 0.0152 1.0000
11.250 1.2426 0.02992 0.02448 -0.0130 0.0150 1.0000
11.500 1.2484 0.03218 0.02689 -0.0106 0.0147 1.0000
11.750 1.2505 0.03466 0.02955 -0.0078 0.0145 1.0000
12.000 1.2475 0.03753 0.03265 -0.0046 0.0144 1.0000
12.250 1.2433 0.03964 0.03498 -0.0014 0.0143 1.0000
12.500 1.2390 0.04163 0.03716 0.0014 0.0143 1.0000
12.750 1.2333 0.04368 0.03940 0.0037 0.0142 1.0000
13.000 1.2255 0.04612 0.04204 0.0054 0.0140 1.0000
13.250 1.2126 0.04968 0.04580 0.0065 0.0140 1.0000
13.500 1.2002 0.05332 0.04964 0.0066 0.0139 1.0000
13.750 1.1835 0.05809 0.05461 0.0055 0.0139 1.0000
14.000 1.1653 0.06386 0.06055 0.0029 0.0140 1.0000
14.250 1.1470 0.07048 0.06737 -0.0014 0.0140 1.0000
14.500 1.1237 0.07903 0.07610 -0.0072 0.0141 1.0000
14.750 1.1016 0.08806 0.08528 -0.0135 0.0141 1.0000
15.000 1.0746 0.09853 0.09589 -0.0204 0.0143 1.0000
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Polar data table (+)
Polar graphs
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