DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Reynolds number: 200,000 Max Cl/Cd: 64.5 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-defcnd2-il-200000-n5.txt Download as CSV file: xf-defcnd2-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DEFIANT CANARD BL110 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3125 0.10109 0.09765 -0.0510 1.0000 0.0198
-10.750 -0.3201 0.09594 0.09257 -0.0528 1.0000 0.0199
-10.500 -0.3192 0.09131 0.08798 -0.0551 0.9909 0.0198
-10.250 -0.3126 0.08579 0.08247 -0.0601 0.9776 0.0196
-10.000 -0.3047 0.08007 0.07674 -0.0660 0.9646 0.0193
-9.750 -0.3015 0.07240 0.06906 -0.0742 0.9508 0.0190
-9.500 -0.3166 0.05778 0.05429 -0.0914 0.9312 0.0185
-9.000 -0.3565 0.04445 0.04025 -0.0974 0.8892 0.0180
-8.750 -0.3691 0.04025 0.03565 -0.0952 0.8748 0.0179
-8.500 -0.3759 0.03654 0.03150 -0.0924 0.8635 0.0180
-8.250 -0.3761 0.03351 0.02804 -0.0896 0.8535 0.0181
-8.000 -0.3697 0.03091 0.02500 -0.0872 0.8455 0.0183
-7.750 -0.3597 0.02865 0.02233 -0.0849 0.8371 0.0186
-7.500 -0.3453 0.02672 0.01999 -0.0831 0.8303 0.0189
-7.250 -0.3284 0.02523 0.01812 -0.0815 0.8230 0.0195
-7.000 -0.3089 0.02385 0.01643 -0.0802 0.8172 0.0201
-6.750 -0.2886 0.02277 0.01527 -0.0793 0.8102 0.0209
-6.500 -0.2666 0.02182 0.01416 -0.0784 0.8035 0.0215
-6.250 -0.2442 0.02084 0.01303 -0.0775 0.7966 0.0220
-6.000 -0.2213 0.01994 0.01198 -0.0766 0.7894 0.0226
-5.750 -0.1982 0.01911 0.01102 -0.0757 0.7824 0.0232
-5.500 -0.1752 0.01837 0.01015 -0.0748 0.7750 0.0240
-5.250 -0.1521 0.01771 0.00938 -0.0738 0.7684 0.0247
-5.000 -0.1302 0.01705 0.00868 -0.0728 0.7606 0.0260
-4.750 -0.1074 0.01656 0.00815 -0.0719 0.7531 0.0276
-4.500 -0.0849 0.01610 0.00762 -0.0709 0.7441 0.0293
-4.250 -0.0623 0.01565 0.00709 -0.0699 0.7352 0.0306
-4.000 -0.0397 0.01521 0.00656 -0.0688 0.7261 0.0324
-3.750 -0.0171 0.01482 0.00614 -0.0678 0.7152 0.0352
-3.500 0.0063 0.01449 0.00575 -0.0668 0.7042 0.0402
-3.250 0.0293 0.01413 0.00536 -0.0658 0.6934 0.0498
-3.000 0.0517 0.01373 0.00501 -0.0648 0.6816 0.0715
-2.750 0.0740 0.01336 0.00473 -0.0638 0.6688 0.1065
-2.500 0.0957 0.01298 0.00449 -0.0627 0.6551 0.1597
-2.250 0.1150 0.01245 0.00426 -0.0613 0.6408 0.2512
-2.000 0.1306 0.01174 0.00405 -0.0592 0.6263 0.3954
-1.750 0.1412 0.01099 0.00403 -0.0557 0.6131 0.5947
-1.500 0.1605 0.01083 0.00406 -0.0536 0.5992 0.6962
-1.250 0.1834 0.01081 0.00404 -0.0522 0.5859 0.7392
-1.000 0.2070 0.01083 0.00402 -0.0510 0.5736 0.7757
-0.750 0.2318 0.01088 0.00403 -0.0500 0.5622 0.8071
-0.500 0.2580 0.01096 0.00405 -0.0494 0.5515 0.8322
-0.250 0.2856 0.01108 0.00410 -0.0490 0.5417 0.8605
0.250 0.3515 0.01147 0.00431 -0.0505 0.5196 0.9086
0.500 0.3851 0.01163 0.00436 -0.0517 0.5091 0.9190
0.750 0.4188 0.01180 0.00440 -0.0530 0.4992 0.9272
1.000 0.4509 0.01192 0.00444 -0.0540 0.4897 0.9363
1.250 0.4862 0.01207 0.00450 -0.0557 0.4807 0.9425
1.500 0.5197 0.01222 0.00456 -0.0571 0.4716 0.9500
1.750 0.5541 0.01236 0.00462 -0.0587 0.4625 0.9563
2.000 0.5889 0.01252 0.00469 -0.0604 0.4537 0.9621
2.250 0.6212 0.01267 0.00478 -0.0615 0.4443 0.9695
2.500 0.6567 0.01283 0.00486 -0.0635 0.4362 0.9748
2.750 0.6888 0.01300 0.00496 -0.0647 0.4284 0.9821
3.000 0.7249 0.01315 0.00506 -0.0668 0.4212 0.9871
3.250 0.7590 0.01332 0.00517 -0.0685 0.4143 0.9931
3.500 0.7941 0.01350 0.00529 -0.0705 0.4088 0.9984
3.750 0.8183 0.01365 0.00543 -0.0701 0.4041 1.0000
4.000 0.8354 0.01381 0.00555 -0.0683 0.4000 1.0000
4.250 0.8526 0.01400 0.00569 -0.0665 0.3963 1.0000
4.500 0.8710 0.01418 0.00587 -0.0649 0.3929 1.0000
4.750 0.8898 0.01437 0.00605 -0.0634 0.3893 1.0000
5.000 0.9087 0.01458 0.00624 -0.0619 0.3859 1.0000
5.250 0.9276 0.01481 0.00644 -0.0604 0.3828 1.0000
5.500 0.9470 0.01505 0.00667 -0.0590 0.3799 1.0000
5.750 0.9671 0.01526 0.00692 -0.0577 0.3768 1.0000
6.000 0.9870 0.01550 0.00718 -0.0564 0.3736 1.0000
6.250 1.0069 0.01576 0.00744 -0.0552 0.3706 1.0000
6.500 1.0270 0.01604 0.00772 -0.0539 0.3677 1.0000
6.750 1.0475 0.01634 0.00801 -0.0528 0.3649 1.0000
7.000 1.0676 0.01659 0.00833 -0.0516 0.3618 1.0000
7.250 1.0874 0.01686 0.00866 -0.0503 0.3584 1.0000
7.500 1.1074 0.01717 0.00900 -0.0491 0.3552 1.0000
7.750 1.1282 0.01751 0.00934 -0.0481 0.3522 1.0000
8.000 1.1489 0.01784 0.00971 -0.0471 0.3493 1.0000
8.250 1.1680 0.01814 0.01013 -0.0458 0.3461 1.0000
8.500 1.1875 0.01847 0.01054 -0.0446 0.3430 1.0000
8.750 1.2072 0.01881 0.01094 -0.0435 0.3399 1.0000
9.000 1.2284 0.01920 0.01135 -0.0426 0.3371 1.0000
9.250 1.2468 0.01957 0.01180 -0.0413 0.3335 1.0000
9.500 1.2582 0.01987 0.01225 -0.0387 0.3284 1.0000
9.750 1.2700 0.02020 0.01262 -0.0362 0.3228 1.0000
10.000 1.2810 0.02055 0.01306 -0.0336 0.3171 1.0000
10.250 1.2917 0.02092 0.01356 -0.0312 0.3109 1.0000
10.500 1.3054 0.02133 0.01404 -0.0293 0.3066 1.0000
10.750 1.3154 0.02175 0.01464 -0.0270 0.2986 1.0000
11.000 1.3266 0.02224 0.01520 -0.0249 0.2927 1.0000
11.250 1.3358 0.02278 0.01587 -0.0228 0.2831 1.0000
11.500 1.3437 0.02345 0.01659 -0.0206 0.2740 1.0000
11.750 1.3480 0.02434 0.01747 -0.0182 0.2636 1.0000
12.000 1.3510 0.02545 0.01857 -0.0160 0.2532 1.0000
12.250 1.3505 0.02689 0.02000 -0.0136 0.2397 1.0000
12.500 1.3555 0.02817 0.02134 -0.0119 0.2301 1.0000
12.750 1.3537 0.02994 0.02312 -0.0100 0.2124 1.0000
13.000 1.3450 0.03234 0.02541 -0.0079 0.1725 1.0000
13.250 1.3307 0.03538 0.02830 -0.0059 0.1522 1.0000
13.500 1.3128 0.03900 0.03183 -0.0043 0.1318 1.0000
13.750 1.3001 0.04247 0.03528 -0.0032 0.1177 1.0000
14.000 1.2884 0.04608 0.03890 -0.0026 0.1060 1.0000
14.250 1.2787 0.04970 0.04256 -0.0023 0.0963 1.0000
14.500 1.2658 0.05389 0.04678 -0.0024 0.0860 1.0000
15.000 1.2459 0.06204 0.05504 -0.0031 0.0719 1.0000
15.250 1.2346 0.06644 0.05949 -0.0037 0.0652 1.0000
15.500 1.2207 0.07127 0.06435 -0.0045 0.0573 1.0000
15.750 1.2144 0.07523 0.06840 -0.0053 0.0530 1.0000
16.250 1.1938 0.08442 0.07768 -0.0073 0.0404 1.0000
16.500 1.1845 0.08901 0.08230 -0.0084 0.0344 1.0000
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Polar data table (+)
Polar graphs
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