NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLR-7223-43 AIRFOIL (nl722343-il) Reynolds number: 200,000 Max Cl/Cd: 53.55 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nl722343-il-200000.txt Download as CSV file: xf-nl722343-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4961 0.08625 0.08264 -0.0286 1.0000 0.0405
-8.500 -0.5014 0.08209 0.07854 -0.0308 1.0000 0.0414
-8.250 -0.5118 0.07766 0.07416 -0.0337 1.0000 0.0417
-8.000 -0.5273 0.07382 0.07035 -0.0353 1.0000 0.0418
-7.750 -0.5369 0.06992 0.06642 -0.0364 1.0000 0.0425
-7.500 -0.5463 0.06617 0.06256 -0.0369 1.0000 0.0439
-7.250 -0.5595 0.06415 0.06014 -0.0360 1.0000 0.0452
-7.000 -0.5627 0.06239 0.05809 -0.0337 1.0000 0.0455
-6.750 -0.5631 0.05540 0.05126 -0.0330 1.0000 0.0466
-6.500 -0.5569 0.05252 0.04846 -0.0314 1.0000 0.0478
-6.250 -0.5506 0.05012 0.04601 -0.0297 1.0000 0.0493
-6.000 -0.5430 0.04767 0.04344 -0.0282 1.0000 0.0518
-5.500 -0.5244 0.04159 0.03673 -0.0255 1.0000 0.0593
-5.250 -0.5109 0.03945 0.03462 -0.0244 1.0000 0.0627
-5.000 -0.4960 0.03740 0.03205 -0.0231 1.0000 0.0717
-4.750 -0.4802 0.03486 0.02962 -0.0224 1.0000 0.0757
-4.500 -0.4624 0.03298 0.02734 -0.0214 1.0000 0.0864
-4.250 -0.4436 0.03082 0.02521 -0.0206 1.0000 0.0914
-4.000 -0.4241 0.02889 0.02308 -0.0200 1.0000 0.1040
-3.750 -0.3827 0.02322 0.01612 -0.0168 1.0000 0.0432
-3.500 -0.3551 0.02111 0.01343 -0.0153 1.0000 0.0364
-3.250 -0.3306 0.01980 0.01196 -0.0144 1.0000 0.0358
-3.000 -0.3064 0.01835 0.01038 -0.0135 1.0000 0.0365
-2.750 -0.2832 0.01711 0.00919 -0.0128 1.0000 0.0389
-2.500 -0.2599 0.01623 0.00829 -0.0118 1.0000 0.0397
-2.250 -0.2368 0.01552 0.00758 -0.0109 1.0000 0.0412
-2.000 -0.2137 0.01494 0.00698 -0.0101 1.0000 0.0437
-1.750 -0.1905 0.01429 0.00634 -0.0094 1.0000 0.0485
-1.500 -0.1596 0.01382 0.00591 -0.0103 0.9981 0.0643
-1.250 -0.1369 0.01202 0.00661 -0.0094 0.9945 0.7306
-1.000 -0.1104 0.01241 0.00715 -0.0077 0.9881 0.7927
-0.750 -0.0884 0.01247 0.00741 -0.0048 0.9808 0.8441
-0.500 -0.0585 0.01248 0.00749 -0.0038 0.9718 0.8825
-0.250 -0.0050 0.01230 0.00724 -0.0081 0.9569 0.8918
0.000 0.0555 0.01193 0.00677 -0.0141 0.9413 0.8923
0.250 0.1048 0.01168 0.00645 -0.0183 0.9335 0.8923
0.500 0.1434 0.01149 0.00622 -0.0203 0.9250 0.8932
0.750 0.1929 0.01120 0.00592 -0.0244 0.9189 0.8933
1.000 0.2322 0.01097 0.00568 -0.0265 0.9103 0.8936
1.250 0.2784 0.01063 0.00535 -0.0298 0.9025 0.8938
1.500 0.3127 0.01038 0.00512 -0.0306 0.8898 0.8950
1.750 0.3474 0.01011 0.00486 -0.0315 0.8750 0.8959
2.000 0.3815 0.00984 0.00461 -0.0322 0.8564 0.8967
2.250 0.4101 0.00962 0.00441 -0.0318 0.8298 0.8979
2.500 0.4400 0.00942 0.00416 -0.0315 0.7899 0.8992
2.750 0.4680 0.00938 0.00379 -0.0305 0.6770 0.9010
3.000 0.4822 0.01029 0.00375 -0.0274 0.4986 0.9039
3.250 0.4967 0.01127 0.00403 -0.0251 0.3649 0.9070
3.500 0.5175 0.01197 0.00435 -0.0242 0.3010 0.9102
3.750 0.5413 0.01249 0.00466 -0.0237 0.2719 0.9135
4.000 0.5666 0.01290 0.00498 -0.0234 0.2543 0.9172
4.250 0.5926 0.01331 0.00534 -0.0232 0.2411 0.9218
4.500 0.6195 0.01369 0.00569 -0.0233 0.2305 0.9275
4.750 0.6483 0.01407 0.00610 -0.0237 0.2213 0.9345
5.000 0.6782 0.01460 0.00658 -0.0244 0.2127 0.9442
5.250 0.7118 0.01493 0.00703 -0.0259 0.2040 0.9585
5.500 0.7464 0.01548 0.00758 -0.0277 0.1953 0.9972
5.750 0.7732 0.01587 0.00803 -0.0279 0.1871 1.0000
6.000 0.7996 0.01636 0.00855 -0.0280 0.1780 1.0000
6.250 0.8249 0.01675 0.00890 -0.0280 0.1664 1.0000
6.500 0.8498 0.01698 0.00917 -0.0279 0.1541 1.0000
6.750 0.8751 0.01718 0.00950 -0.0277 0.1426 1.0000
7.000 0.9001 0.01742 0.00982 -0.0275 0.1299 1.0000
7.250 0.9250 0.01753 0.01001 -0.0273 0.1139 1.0000
7.500 0.9500 0.01774 0.01017 -0.0270 0.0859 1.0000
7.750 0.9696 0.01900 0.01127 -0.0259 0.0598 1.0000
8.000 0.9889 0.02029 0.01255 -0.0247 0.0500 1.0000
8.250 1.0064 0.02181 0.01402 -0.0233 0.0447 1.0000
8.500 1.0278 0.02282 0.01519 -0.0224 0.0408 1.0000
8.750 1.0467 0.02411 0.01647 -0.0213 0.0377 1.0000
9.000 1.0654 0.02599 0.01844 -0.0202 0.0358 1.0000
9.250 1.0856 0.02752 0.02016 -0.0191 0.0344 1.0000
9.500 1.1048 0.02924 0.02208 -0.0180 0.0332 1.0000
9.750 1.1227 0.03112 0.02417 -0.0168 0.0323 1.0000
10.000 1.1391 0.03301 0.02622 -0.0155 0.0313 1.0000
10.250 1.1541 0.03515 0.02850 -0.0143 0.0304 1.0000
10.500 1.1633 0.03895 0.03254 -0.0128 0.0295 1.0000
10.750 1.1682 0.04154 0.03549 -0.0104 0.0291 1.0000
11.000 1.1691 0.04429 0.03862 -0.0077 0.0290 1.0000
11.250 1.1650 0.04740 0.04207 -0.0048 0.0289 1.0000
11.500 1.1536 0.05032 0.04529 -0.0012 0.0289 1.0000
11.750 1.1388 0.05359 0.04881 0.0019 0.0290 1.0000
12.000 1.1215 0.05721 0.05265 0.0042 0.0290 1.0000
12.250 1.1019 0.06129 0.05695 0.0053 0.0291 1.0000
12.500 1.0820 0.06621 0.06205 0.0050 0.0293 1.0000
12.750 1.0629 0.07137 0.06740 0.0035 0.0294 1.0000
13.000 1.0414 0.07719 0.07341 -0.0001 0.0296 1.0000
13.250 1.0149 0.08547 0.08191 -0.0072 0.0299 1.0000
13.500 0.6957 0.13563 0.13262 -0.0368 0.0457 1.0000
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Polar data table (+)
Polar graphs
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