DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Reynolds number: 500,000 Max Cl/Cd: 89.6 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-defcnd2-il-500000.txt Download as CSV file: xf-defcnd2-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.2057 0.12265 0.12061 -0.0454 1.0000 0.0209
-12.500 -0.3128 0.12423 0.12195 -0.0431 1.0000 0.0203
-12.250 -0.3062 0.12171 0.11945 -0.0433 1.0000 0.0206
-12.000 -0.3012 0.11885 0.11661 -0.0439 1.0000 0.0208
-11.750 -0.2959 0.11617 0.11395 -0.0443 1.0000 0.0211
-11.500 -0.2923 0.11321 0.11101 -0.0450 1.0000 0.0216
-11.250 -0.2903 0.10998 0.10780 -0.0459 1.0000 0.0219
-11.000 -0.1809 0.08762 0.08555 -0.0689 0.9556 0.0257
-10.750 -0.1612 0.08428 0.08218 -0.0721 0.9453 0.0263
-10.500 -0.1445 0.08030 0.07816 -0.0760 0.9340 0.0270
-10.250 -0.1348 0.07545 0.07326 -0.0800 0.9209 0.0277
-10.000 -0.2773 0.07984 0.07775 -0.0710 0.9593 0.0259
-9.750 -0.2516 0.07636 0.07423 -0.0769 0.9500 0.0266
-9.500 -0.2298 0.07026 0.06809 -0.0866 0.9375 0.0272
-9.250 -0.2244 0.05947 0.05716 -0.1032 0.9129 0.0278
-9.000 -0.2465 0.05326 0.05072 -0.1075 0.8853 0.0278
-8.750 -0.2693 0.04997 0.04724 -0.1049 0.8681 0.0279
-8.500 -0.2823 0.04718 0.04427 -0.1022 0.8566 0.0286
-8.250 -0.2867 0.03365 0.03037 -0.0921 0.8327 0.0315
-8.000 -0.2926 0.03089 0.02738 -0.0893 0.8256 0.0316
-7.000 -0.3039 0.02347 0.01820 -0.0824 0.8131 0.0230
-6.750 -0.2917 0.01964 0.01371 -0.0794 0.8072 0.0213
-6.250 -0.2467 0.01733 0.01106 -0.0774 0.7952 0.0216
-6.000 -0.2231 0.01645 0.01006 -0.0766 0.7893 0.0220
-5.750 -0.1991 0.01568 0.00919 -0.0759 0.7832 0.0225
-5.500 -0.1753 0.01497 0.00839 -0.0751 0.7766 0.0231
-5.250 -0.1511 0.01439 0.00770 -0.0743 0.7707 0.0238
-5.000 -0.1269 0.01394 0.00719 -0.0735 0.7628 0.0248
-4.750 -0.1032 0.01345 0.00659 -0.0726 0.7548 0.0253
-4.500 -0.0832 0.01254 0.00564 -0.0711 0.7455 0.0263
-4.250 -0.0605 0.01208 0.00514 -0.0700 0.7365 0.0274
-4.000 -0.0371 0.01172 0.00473 -0.0691 0.7267 0.0288
-3.750 -0.0133 0.01139 0.00436 -0.0682 0.7161 0.0303
-3.500 0.0105 0.01109 0.00398 -0.0673 0.7054 0.0325
-3.250 0.0340 0.01077 0.00363 -0.0664 0.6933 0.0361
-3.000 0.0580 0.01053 0.00332 -0.0655 0.6796 0.0416
-2.750 0.0797 0.01011 0.00302 -0.0643 0.6646 0.0768
-2.500 0.1003 0.00967 0.00282 -0.0630 0.6484 0.1519
-2.250 0.1206 0.00927 0.00265 -0.0617 0.6317 0.2393
-2.000 0.1392 0.00878 0.00251 -0.0601 0.6155 0.3584
-1.750 0.1530 0.00809 0.00238 -0.0576 0.6008 0.5350
-1.500 0.1693 0.00779 0.00242 -0.0551 0.5865 0.6632
-1.250 0.1910 0.00777 0.00243 -0.0537 0.5730 0.7128
-1.000 0.2129 0.00777 0.00246 -0.0523 0.5602 0.7530
-0.750 0.2364 0.00780 0.00247 -0.0512 0.5485 0.7796
-0.500 0.2599 0.00782 0.00251 -0.0501 0.5384 0.8078
-0.250 0.2834 0.00787 0.00256 -0.0490 0.5292 0.8341
0.000 0.3080 0.00792 0.00260 -0.0482 0.5195 0.8563
0.250 0.3333 0.00799 0.00265 -0.0475 0.5104 0.8763
0.500 0.3598 0.00809 0.00273 -0.0471 0.5003 0.8962
0.750 0.3886 0.00819 0.00283 -0.0471 0.4896 0.9199
1.000 0.4206 0.00836 0.00295 -0.0478 0.4783 0.9388
1.250 0.4579 0.00856 0.00306 -0.0498 0.4663 0.9479
1.500 0.4927 0.00874 0.00315 -0.0514 0.4543 0.9559
1.750 0.5317 0.00892 0.00325 -0.0539 0.4419 0.9604
2.000 0.5663 0.00910 0.00335 -0.0555 0.4324 0.9672
2.250 0.6047 0.00930 0.00345 -0.0580 0.4241 0.9706
2.500 0.6439 0.00945 0.00355 -0.0606 0.4168 0.9740
2.750 0.6795 0.00965 0.00367 -0.0625 0.4105 0.9793
3.000 0.7164 0.00980 0.00378 -0.0647 0.4054 0.9835
3.250 0.7554 0.00995 0.00388 -0.0674 0.4007 0.9867
3.500 0.7923 0.01013 0.00400 -0.0696 0.3965 0.9909
3.750 0.8296 0.01028 0.00413 -0.0720 0.3931 0.9946
4.000 0.8687 0.01040 0.00424 -0.0747 0.3896 0.9978
4.250 0.9025 0.01053 0.00436 -0.0764 0.3862 1.0000
4.500 0.9185 0.01066 0.00446 -0.0743 0.3836 1.0000
4.750 0.9349 0.01084 0.00459 -0.0723 0.3807 1.0000
5.000 0.9534 0.01094 0.00472 -0.0707 0.3784 1.0000
5.250 0.9721 0.01106 0.00487 -0.0691 0.3758 1.0000
5.500 0.9907 0.01121 0.00502 -0.0674 0.3729 1.0000
5.750 1.0093 0.01140 0.00520 -0.0658 0.3700 1.0000
6.000 1.0281 0.01164 0.00540 -0.0643 0.3671 1.0000
6.250 1.0479 0.01183 0.00562 -0.0629 0.3646 1.0000
6.500 1.0679 0.01198 0.00581 -0.0615 0.3619 1.0000
6.750 1.0877 0.01215 0.00601 -0.0601 0.3589 1.0000
7.000 1.1074 0.01236 0.00623 -0.0588 0.3559 1.0000
7.250 1.1273 0.01264 0.00650 -0.0575 0.3527 1.0000
7.500 1.1479 0.01290 0.00677 -0.0563 0.3495 1.0000
7.750 1.1672 0.01306 0.00701 -0.0549 0.3464 1.0000
8.000 1.1864 0.01326 0.00725 -0.0534 0.3428 1.0000
8.250 1.2044 0.01352 0.00751 -0.0518 0.3381 1.0000
8.500 1.2215 0.01377 0.00779 -0.0501 0.3330 1.0000
8.750 1.2328 0.01385 0.00794 -0.0470 0.3266 1.0000
9.000 1.2461 0.01412 0.00818 -0.0446 0.3213 1.0000
9.250 1.2604 0.01423 0.00839 -0.0422 0.3153 1.0000
9.500 1.2766 0.01442 0.00863 -0.0404 0.3100 1.0000
9.750 1.2921 0.01465 0.00890 -0.0385 0.3039 1.0000
10.000 1.3093 0.01483 0.00915 -0.0370 0.2956 1.0000
10.250 1.3257 0.01510 0.00945 -0.0354 0.2877 1.0000
10.500 1.3396 0.01547 0.00983 -0.0335 0.2769 1.0000
10.750 1.3502 0.01604 0.01035 -0.0313 0.2657 1.0000
11.000 1.3593 0.01678 0.01104 -0.0291 0.2539 1.0000
11.250 1.3706 0.01748 0.01176 -0.0272 0.2445 1.0000
11.500 1.3797 0.01834 0.01260 -0.0252 0.2373 1.0000
11.750 1.3919 0.01909 0.01339 -0.0237 0.2271 1.0000
12.000 1.4026 0.01995 0.01428 -0.0221 0.2147 1.0000
12.250 1.3968 0.02188 0.01594 -0.0192 0.1651 1.0000
12.500 1.3908 0.02397 0.01790 -0.0166 0.1420 1.0000
12.750 1.3789 0.02662 0.02043 -0.0138 0.1169 1.0000
13.000 1.3695 0.02927 0.02299 -0.0116 0.0959 1.0000
13.250 1.3623 0.03188 0.02554 -0.0099 0.0809 1.0000
13.500 1.3527 0.03487 0.02848 -0.0085 0.0651 1.0000
13.750 1.3439 0.03799 0.03157 -0.0074 0.0523 1.0000
14.000 1.3312 0.04171 0.03526 -0.0066 0.0394 1.0000
14.250 1.3189 0.04563 0.03917 -0.0062 0.0295 1.0000
14.500 1.2980 0.05074 0.04427 -0.0061 0.0184 1.0000
14.750 1.2910 0.05445 0.04804 -0.0062 0.0155 1.0000
15.000 1.2824 0.05842 0.05208 -0.0065 0.0132 1.0000
15.250 1.2713 0.06278 0.05652 -0.0069 0.0114 1.0000
15.500 1.2625 0.06692 0.06076 -0.0074 0.0101 1.0000
15.750 1.2581 0.07055 0.06449 -0.0079 0.0100 1.0000
16.000 1.2509 0.07461 0.06864 -0.0085 0.0095 1.0000
16.250 1.2443 0.07867 0.07279 -0.0092 0.0093 1.0000
16.500 1.2342 0.08323 0.07744 -0.0101 0.0088 1.0000
16.750 1.2275 0.08742 0.08172 -0.0110 0.0087 1.0000
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