ONERA HOR07 AIRFOIL (hor07-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA HOR07 AIRFOIL (hor07-il) Reynolds number: 200,000 Max Cl/Cd: 72.98 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hor07-il-200000-n5.txt Download as CSV file: xf-hor07-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ONERA HOR07 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4340 0.11023 0.10677 -0.0020 1.0000 0.0283
-8.500 -0.4298 0.10696 0.10353 -0.0050 1.0000 0.0285
-8.250 -0.4243 0.10351 0.10011 -0.0075 1.0000 0.0286
-8.000 -0.4190 0.10003 0.09666 -0.0098 1.0000 0.0287
-7.750 -0.4120 0.09644 0.09311 -0.0124 1.0000 0.0288
-7.500 -0.4016 0.09250 0.08919 -0.0158 1.0000 0.0288
-7.250 -0.3896 0.08839 0.08510 -0.0195 1.0000 0.0288
-6.750 -0.3718 0.07812 0.07485 -0.0232 1.0000 0.0210
-6.500 -0.3564 0.07405 0.07079 -0.0273 1.0000 0.0207
-6.250 -0.3275 0.06733 0.06402 -0.0378 0.9698 0.0214
-6.000 -0.2966 0.06155 0.05815 -0.0463 0.9345 0.0213
-5.750 -0.2696 0.05684 0.05332 -0.0522 0.9027 0.0208
-5.500 -0.2400 0.05142 0.04773 -0.0591 0.8767 0.0202
-5.250 -0.2040 0.04427 0.04031 -0.0679 0.8576 0.0195
-4.750 -0.1073 0.02150 0.01530 -0.0899 0.8288 0.0184
-4.500 -0.0769 0.01951 0.01275 -0.0907 0.8092 0.0188
-4.250 -0.0472 0.01807 0.01088 -0.0912 0.7917 0.0194
-4.000 -0.0178 0.01694 0.00940 -0.0915 0.7770 0.0202
-3.750 0.0116 0.01606 0.00823 -0.0917 0.7650 0.0211
-3.500 0.0407 0.01532 0.00732 -0.0919 0.7541 0.0230
-3.250 0.0696 0.01488 0.00677 -0.0921 0.7432 0.0254
-3.000 0.0991 0.01434 0.00606 -0.0923 0.7330 0.0277
-2.750 0.1286 0.01378 0.00536 -0.0926 0.7237 0.0314
-2.500 0.1581 0.01341 0.00485 -0.0927 0.7142 0.0380
-2.250 0.1874 0.01304 0.00441 -0.0930 0.7054 0.0497
-2.000 0.2165 0.01266 0.00412 -0.0932 0.6962 0.0744
-1.750 0.2455 0.01243 0.00396 -0.0934 0.6867 0.1096
-1.500 0.2741 0.01233 0.00383 -0.0935 0.6770 0.1357
-1.250 0.3028 0.01226 0.00373 -0.0936 0.6665 0.1584
-1.000 0.3316 0.01219 0.00362 -0.0937 0.6567 0.1742
-0.750 0.3602 0.01213 0.00353 -0.0937 0.6474 0.1907
-0.500 0.3889 0.01206 0.00350 -0.0938 0.6374 0.2139
-0.250 0.4176 0.01200 0.00343 -0.0939 0.6278 0.2334
0.000 0.4462 0.01195 0.00337 -0.0940 0.6181 0.2521
0.250 0.4749 0.01188 0.00334 -0.0941 0.6082 0.2743
0.500 0.5035 0.01183 0.00332 -0.0942 0.5990 0.3011
0.750 0.5320 0.01177 0.00331 -0.0943 0.5894 0.3343
1.000 0.5605 0.01166 0.00335 -0.0944 0.5800 0.4027
1.250 0.5866 0.01095 0.00340 -0.0941 0.5711 0.6766
1.500 0.6095 0.01041 0.00322 -0.0925 0.5614 1.0000
1.750 0.6380 0.01054 0.00327 -0.0925 0.5513 1.0000
2.000 0.6664 0.01068 0.00333 -0.0926 0.5406 1.0000
2.250 0.6948 0.01081 0.00341 -0.0926 0.5292 1.0000
2.500 0.7232 0.01095 0.00351 -0.0926 0.5182 1.0000
2.750 0.7514 0.01111 0.00364 -0.0926 0.5077 1.0000
3.000 0.7796 0.01128 0.00377 -0.0926 0.4971 1.0000
3.250 0.8078 0.01145 0.00393 -0.0927 0.4868 1.0000
3.500 0.8358 0.01164 0.00410 -0.0927 0.4763 1.0000
3.750 0.8634 0.01187 0.00429 -0.0926 0.4589 1.0000
4.000 0.8904 0.01220 0.00447 -0.0925 0.4293 1.0000
4.250 0.9171 0.01258 0.00469 -0.0924 0.3936 1.0000
4.500 0.9437 0.01299 0.00495 -0.0923 0.3577 1.0000
4.750 0.9697 0.01354 0.00530 -0.0922 0.3142 1.0000
5.000 0.9954 0.01415 0.00570 -0.0921 0.2495 1.0000
5.250 1.0180 0.01553 0.00651 -0.0920 0.1698 1.0000
5.500 1.0425 0.01641 0.00723 -0.0918 0.1010 1.0000
5.750 1.0660 0.01747 0.00808 -0.0916 0.0647 1.0000
6.000 1.0907 0.01820 0.00880 -0.0912 0.0524 1.0000
6.250 1.1153 0.01887 0.00950 -0.0909 0.0460 1.0000
6.500 1.1391 0.01966 0.01032 -0.0905 0.0420 1.0000
6.750 1.1632 0.02033 0.01113 -0.0900 0.0401 1.0000
7.000 1.1864 0.02108 0.01199 -0.0895 0.0384 1.0000
7.250 1.2088 0.02190 0.01291 -0.0888 0.0369 1.0000
7.500 1.2303 0.02280 0.01389 -0.0881 0.0357 1.0000
7.750 1.2508 0.02378 0.01496 -0.0872 0.0347 1.0000
8.000 1.2698 0.02491 0.01618 -0.0862 0.0338 1.0000
8.250 1.2869 0.02625 0.01759 -0.0849 0.0330 1.0000
8.500 1.3021 0.02788 0.01929 -0.0833 0.0322 1.0000
8.750 1.3205 0.02902 0.02054 -0.0821 0.0317 1.0000
9.000 1.3395 0.02996 0.02161 -0.0810 0.0306 1.0000
9.250 1.3579 0.03086 0.02268 -0.0799 0.0289 1.0000
9.500 1.3748 0.03182 0.02376 -0.0788 0.0273 1.0000
9.750 1.3902 0.03285 0.02486 -0.0774 0.0259 1.0000
10.000 1.4025 0.03418 0.02624 -0.0758 0.0245 1.0000
10.250 1.4134 0.03582 0.02801 -0.0740 0.0232 1.0000
10.500 1.4253 0.03692 0.02932 -0.0722 0.0220 1.0000
10.750 1.4331 0.03826 0.03085 -0.0700 0.0208 1.0000
11.000 1.4395 0.03977 0.03253 -0.0679 0.0196 1.0000
11.250 1.4451 0.04136 0.03425 -0.0661 0.0187 1.0000
11.500 1.4493 0.04321 0.03618 -0.0647 0.0179 1.0000
11.750 1.4511 0.04573 0.03882 -0.0632 0.0170 1.0000
12.000 1.4547 0.04825 0.04165 -0.0619 0.0160 1.0000
12.250 1.4560 0.05104 0.04471 -0.0608 0.0150 1.0000
12.500 1.4565 0.05384 0.04771 -0.0601 0.0142 1.0000
12.750 1.4569 0.05657 0.05060 -0.0599 0.0135 1.0000
13.000 1.4572 0.05935 0.05349 -0.0600 0.0130 1.0000
13.250 1.4562 0.06239 0.05663 -0.0603 0.0126 1.0000
13.500 1.4522 0.06596 0.06032 -0.0607 0.0123 1.0000
13.750 1.4431 0.07068 0.06535 -0.0610 0.0118 1.0000
14.000 1.4309 0.07595 0.07092 -0.0617 0.0115 1.0000
14.250 1.4164 0.08174 0.07701 -0.0630 0.0112 1.0000
14.500 1.3998 0.08802 0.08354 -0.0649 0.0110 1.0000
14.750 1.3815 0.09491 0.09068 -0.0674 0.0109 1.0000
15.000 1.3616 0.10259 0.09857 -0.0709 0.0108 1.0000
15.250 1.3400 0.11113 0.10734 -0.0752 0.0108 1.0000
15.500 1.3166 0.12074 0.11717 -0.0806 0.0109 1.0000
15.750 1.2913 0.13151 0.12815 -0.0871 0.0110 1.0000
16.000 1.2628 0.14414 0.14097 -0.0951 0.0113 1.0000
16.250 1.2322 0.15908 0.15604 -0.1047 0.0117 1.0000
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Polar data table (+)
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