NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLR-7223-43 AIRFOIL (nl722343-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.1 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nl722343-il-1000000-n5.txt Download as CSV file: xf-nl722343-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5303 0.08391 0.08221 -0.0271 1.0000 0.0051
-9.250 -0.5340 0.07941 0.07773 -0.0295 1.0000 0.0052
-9.000 -0.5451 0.07353 0.07189 -0.0336 1.0000 0.0051
-8.750 -0.5689 0.06764 0.06601 -0.0378 1.0000 0.0051
-8.500 -0.5908 0.06321 0.06154 -0.0381 1.0000 0.0051
-8.250 -0.5882 0.05536 0.05351 -0.0446 0.9970 0.0050
-8.000 -0.5817 0.04699 0.04487 -0.0493 0.9923 0.0049
-7.750 -0.6092 0.01924 0.01514 -0.0510 0.9806 0.0056
-7.500 -0.5831 0.01759 0.01321 -0.0513 0.9774 0.0058
-7.250 -0.5547 0.01639 0.01182 -0.0519 0.9752 0.0058
-6.750 -0.5023 0.01371 0.00876 -0.0523 0.9678 0.0061
-6.500 -0.4734 0.01300 0.00797 -0.0528 0.9645 0.0063
-6.250 -0.4432 0.01237 0.00727 -0.0536 0.9618 0.0064
-6.000 -0.4129 0.01195 0.00680 -0.0543 0.9588 0.0067
-5.750 -0.3848 0.01140 0.00618 -0.0546 0.9539 0.0069
-5.500 -0.3550 0.01092 0.00564 -0.0551 0.9498 0.0072
-5.250 -0.3250 0.01035 0.00500 -0.0557 0.9462 0.0074
-5.000 -0.2973 0.00990 0.00450 -0.0558 0.9408 0.0077
-4.750 -0.2689 0.00950 0.00404 -0.0560 0.9358 0.0079
-4.250 -0.2139 0.00874 0.00319 -0.0560 0.9263 0.0086
-4.000 -0.1863 0.00848 0.00290 -0.0560 0.9202 0.0090
-3.750 -0.1589 0.00825 0.00264 -0.0559 0.9138 0.0094
-3.500 -0.1321 0.00805 0.00240 -0.0557 0.9061 0.0098
-3.250 -0.1048 0.00788 0.00218 -0.0555 0.9003 0.0103
-3.000 -0.0781 0.00771 0.00199 -0.0552 0.8927 0.0110
-2.750 -0.0521 0.00756 0.00180 -0.0547 0.8776 0.0123
-2.500 -0.0268 0.00747 0.00161 -0.0540 0.8534 0.0138
-2.250 -0.0021 0.00740 0.00144 -0.0532 0.8219 0.0169
-2.000 0.0234 0.00732 0.00130 -0.0526 0.7977 0.0253
-1.750 0.0493 0.00718 0.00119 -0.0521 0.7804 0.0489
-1.500 0.0747 0.00695 0.00108 -0.0517 0.7619 0.1045
-1.000 0.1155 0.00610 0.00082 -0.0494 0.6363 0.4428
-0.750 0.1353 0.00586 0.00098 -0.0480 0.5712 0.6635
-0.500 0.1595 0.00625 0.00113 -0.0472 0.5068 0.6829
-0.250 0.1841 0.00658 0.00126 -0.0464 0.4483 0.6948
0.000 0.2095 0.00687 0.00134 -0.0459 0.3957 0.6998
0.250 0.2354 0.00712 0.00138 -0.0455 0.3501 0.7016
0.500 0.2615 0.00733 0.00142 -0.0452 0.3094 0.7020
0.750 0.2877 0.00753 0.00146 -0.0449 0.2736 0.7022
1.000 0.3141 0.00773 0.00151 -0.0447 0.2412 0.7024
1.250 0.3406 0.00791 0.00157 -0.0444 0.2142 0.7026
1.500 0.3674 0.00806 0.00162 -0.0442 0.1959 0.7028
2.000 0.4215 0.00830 0.00175 -0.0439 0.1727 0.7033
2.250 0.4486 0.00841 0.00182 -0.0437 0.1652 0.7037
2.500 0.4757 0.00851 0.00190 -0.0436 0.1594 0.7040
2.750 0.5026 0.00864 0.00199 -0.0434 0.1525 0.7043
3.000 0.5297 0.00874 0.00209 -0.0432 0.1470 0.7047
3.250 0.5566 0.00886 0.00219 -0.0431 0.1426 0.7052
3.500 0.5835 0.00899 0.00230 -0.0429 0.1381 0.7057
3.750 0.6106 0.00909 0.00242 -0.0427 0.1353 0.7061
4.000 0.6375 0.00920 0.00254 -0.0425 0.1322 0.7065
4.250 0.6641 0.00935 0.00267 -0.0423 0.1279 0.7069
4.500 0.6908 0.00949 0.00281 -0.0421 0.1235 0.7073
4.750 0.7176 0.00961 0.00294 -0.0419 0.1183 0.7077
5.000 0.7438 0.00979 0.00309 -0.0417 0.1109 0.7081
5.250 0.7703 0.00993 0.00323 -0.0414 0.1026 0.7085
5.500 0.7958 0.01019 0.00341 -0.0411 0.0873 0.7090
5.750 0.8208 0.01051 0.00366 -0.0407 0.0708 0.7095
6.000 0.8456 0.01086 0.00394 -0.0402 0.0574 0.7099
6.250 0.8701 0.01123 0.00426 -0.0397 0.0451 0.7105
6.500 0.8944 0.01164 0.00461 -0.0392 0.0321 0.7110
6.750 0.9186 0.01207 0.00498 -0.0386 0.0228 0.7115
7.000 0.9432 0.01243 0.00534 -0.0381 0.0184 0.7121
7.250 0.9681 0.01275 0.00569 -0.0377 0.0164 0.7127
7.500 0.9926 0.01313 0.00608 -0.0371 0.0144 0.7133
7.750 1.0174 0.01344 0.00644 -0.0367 0.0135 0.7139
8.000 1.0418 0.01380 0.00683 -0.0362 0.0126 0.7146
8.250 1.0658 0.01421 0.00727 -0.0356 0.0116 0.7153
8.500 1.0896 0.01463 0.00774 -0.0351 0.0108 0.7159
8.750 1.1137 0.01501 0.00817 -0.0345 0.0104 0.7166
9.000 1.1373 0.01542 0.00863 -0.0339 0.0099 0.7173
9.250 1.1607 0.01585 0.00912 -0.0333 0.0094 0.7180
9.500 1.1835 0.01633 0.00965 -0.0326 0.0090 0.7189
9.750 1.2056 0.01687 0.01026 -0.0318 0.0087 0.7198
10.000 1.2266 0.01752 0.01099 -0.0309 0.0083 0.7209
10.250 1.2484 0.01804 0.01160 -0.0300 0.0081 0.7220
10.500 1.2697 0.01858 0.01222 -0.0292 0.0079 0.7231
10.750 1.2902 0.01918 0.01291 -0.0282 0.0078 0.7244
11.000 1.3103 0.01980 0.01362 -0.0272 0.0075 0.7258
11.250 1.3295 0.02046 0.01438 -0.0260 0.0074 0.7273
11.500 1.3484 0.02112 0.01512 -0.0248 0.0072 0.7288
11.750 1.3661 0.02185 0.01594 -0.0235 0.0070 0.7304
12.000 1.3829 0.02260 0.01678 -0.0221 0.0069 0.7320
12.500 1.4132 0.02419 0.01857 -0.0189 0.0066 0.7361
12.750 1.4251 0.02504 0.01953 -0.0167 0.0065 0.7386
13.000 1.4332 0.02595 0.02053 -0.0140 0.0063 0.7415
13.250 1.4374 0.02707 0.02178 -0.0109 0.0062 0.7449
13.750 1.4395 0.02979 0.02476 -0.0046 0.0060 0.7534
14.000 1.4403 0.03124 0.02635 -0.0020 0.0060 0.7591
14.250 1.4441 0.03256 0.02780 0.0001 0.0059 0.7660
14.500 1.4424 0.03434 0.02975 0.0024 0.0059 0.7756
14.750 1.4398 0.03629 0.03187 0.0043 0.0058 0.7918
15.000 1.4340 0.03822 0.03429 0.0062 0.0058 0.9382
15.250 1.4297 0.04151 0.03776 0.0058 0.0058 1.0000
15.500 1.4184 0.04523 0.04163 0.0058 0.0058 1.0000
15.750 1.4067 0.04961 0.04617 0.0046 0.0057 1.0000
16.000 1.3894 0.05571 0.05243 0.0015 0.0057 1.0000
16.250 1.3600 0.06547 0.06239 -0.0049 0.0058 1.0000
16.500 1.3226 0.07795 0.07509 -0.0130 0.0058 1.0000
16.750 1.2812 0.09075 0.08806 -0.0205 0.0058 1.0000
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Polar data table (+)
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