GIII BL207 AIRFOIL (giiih-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL207 AIRFOIL (giiih-il) Reynolds number: 200,000 Max Cl/Cd: 62.01 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiih-il-200000.txt Download as CSV file: xf-giiih-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL207 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4565 0.10730 0.10391 -0.0086 1.0000 0.0392
-10.000 -0.4621 0.10331 0.09996 -0.0116 1.0000 0.0399
-9.750 -0.5717 0.10892 0.10538 0.0027 1.0000 0.0357
-9.500 -0.5701 0.10482 0.10130 0.0004 1.0000 0.0368
-9.250 -0.5692 0.10056 0.09707 -0.0024 1.0000 0.0379
-9.000 -0.5697 0.09603 0.09258 -0.0068 1.0000 0.0390
-8.750 -0.5722 0.09089 0.08748 -0.0137 1.0000 0.0397
-8.500 -0.5777 0.08588 0.08248 -0.0202 1.0000 0.0400
-8.250 -0.5806 0.08163 0.07812 -0.0242 1.0000 0.0403
-8.000 -0.5788 0.07776 0.07412 -0.0262 1.0000 0.0405
-7.750 -0.5223 0.05874 0.05539 -0.0306 1.0000 0.0421
-7.500 -0.5180 0.05484 0.05150 -0.0300 1.0000 0.0430
-7.250 -0.5149 0.05097 0.04759 -0.0297 1.0000 0.0441
-7.000 -0.5116 0.04702 0.04358 -0.0295 1.0000 0.0456
-6.750 -0.5076 0.04304 0.03949 -0.0291 1.0000 0.0474
-6.500 -0.5025 0.03923 0.03548 -0.0284 1.0000 0.0507
-6.250 -0.4969 0.03863 0.03424 -0.0252 1.0000 0.0537
-5.750 -0.5092 0.04191 0.03723 -0.0236 1.0000 0.0578
-5.500 -0.4972 0.03953 0.03472 -0.0218 1.0000 0.0608
-4.250 -0.4303 0.02501 0.01842 -0.0088 1.0000 0.0478
-4.000 -0.4108 0.02279 0.01585 -0.0071 1.0000 0.0472
-3.750 -0.3868 0.02010 0.01261 -0.0055 1.0000 0.0439
-3.500 -0.3517 0.01834 0.01062 -0.0068 0.9974 0.0451
-3.250 -0.3133 0.01713 0.00926 -0.0089 0.9943 0.0490
-3.000 -0.2759 0.01641 0.00834 -0.0107 0.9896 0.0538
-2.750 -0.2406 0.01474 0.00674 -0.0125 0.9860 0.0609
-2.500 -0.2020 0.01386 0.00588 -0.0150 0.9825 0.0728
-2.250 -0.1683 0.01315 0.00520 -0.0165 0.9759 0.0863
-2.000 -0.1298 0.01255 0.00464 -0.0190 0.9713 0.1088
-1.750 -0.1111 0.00962 0.00437 -0.0181 0.9664 0.7347
-1.500 -0.0866 0.00956 0.00465 -0.0156 0.9599 0.8676
-1.250 -0.0512 0.00974 0.00480 -0.0158 0.9564 0.9162
-1.000 -0.0047 0.01001 0.00500 -0.0183 0.9553 0.9517
-0.750 0.0739 0.01028 0.00516 -0.0276 0.9621 0.9818
-0.500 0.1360 0.01015 0.00495 -0.0348 0.9614 0.9913
-0.250 0.1827 0.00996 0.00470 -0.0389 0.9530 0.9944
0.000 0.2255 0.00973 0.00443 -0.0420 0.9412 0.9973
0.250 0.2589 0.00959 0.00426 -0.0434 0.9281 1.0000
0.500 0.2817 0.00951 0.00415 -0.0425 0.9140 1.0000
0.750 0.3032 0.00946 0.00407 -0.0414 0.9002 1.0000
1.000 0.3245 0.00941 0.00402 -0.0401 0.8866 1.0000
1.250 0.3463 0.00938 0.00398 -0.0390 0.8734 1.0000
1.500 0.3684 0.00937 0.00396 -0.0379 0.8606 1.0000
1.750 0.3904 0.00937 0.00396 -0.0368 0.8478 1.0000
2.000 0.4126 0.00937 0.00397 -0.0356 0.8350 1.0000
2.250 0.4349 0.00939 0.00401 -0.0344 0.8219 1.0000
2.500 0.4574 0.00941 0.00404 -0.0332 0.8080 1.0000
2.750 0.4785 0.00935 0.00396 -0.0314 0.7878 1.0000
3.000 0.4989 0.00926 0.00383 -0.0294 0.7598 1.0000
3.250 0.5207 0.00924 0.00381 -0.0278 0.7328 1.0000
3.500 0.5429 0.00925 0.00379 -0.0263 0.7031 1.0000
3.750 0.5650 0.00931 0.00380 -0.0248 0.6666 1.0000
4.000 0.5866 0.00946 0.00384 -0.0233 0.6194 1.0000
4.250 0.6064 0.00978 0.00390 -0.0215 0.5398 1.0000
4.500 0.6218 0.01058 0.00413 -0.0191 0.4139 1.0000
4.750 0.6339 0.01199 0.00468 -0.0168 0.2444 1.0000
5.000 0.6452 0.01391 0.00568 -0.0146 0.0985 1.0000
5.250 0.6637 0.01502 0.00666 -0.0131 0.0743 1.0000
5.500 0.6829 0.01607 0.00767 -0.0117 0.0621 1.0000
5.750 0.7039 0.01698 0.00862 -0.0105 0.0549 1.0000
6.000 0.7235 0.01838 0.01003 -0.0092 0.0494 1.0000
6.250 0.7462 0.01930 0.01104 -0.0083 0.0445 1.0000
6.500 0.7684 0.02069 0.01243 -0.0074 0.0413 1.0000
6.750 0.7911 0.02339 0.01524 -0.0065 0.0388 1.0000
7.000 0.8148 0.02427 0.01637 -0.0056 0.0360 1.0000
7.250 0.8378 0.02626 0.01866 -0.0046 0.0343 1.0000
7.500 0.8593 0.02878 0.02152 -0.0033 0.0335 1.0000
7.750 0.8780 0.03197 0.02515 -0.0017 0.0333 1.0000
8.000 0.8966 0.03391 0.02726 -0.0008 0.0314 1.0000
8.250 0.9112 0.03685 0.03037 0.0001 0.0296 1.0000
8.500 0.9102 0.04462 0.03929 0.0044 0.0353 1.0000
9.250 0.8093 0.05570 0.05208 0.0167 0.0604 1.0000
9.500 0.7856 0.05974 0.05626 0.0184 0.0601 1.0000
9.750 0.7597 0.06448 0.06111 0.0183 0.0604 1.0000
10.000 0.7348 0.07013 0.06682 0.0167 0.0611 1.0000
10.250 0.7114 0.07666 0.07340 0.0140 0.0618 1.0000
10.500 0.6920 0.08366 0.08042 0.0108 0.0623 1.0000
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Polar data table (+)
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