GIII BL288 AIRFOIL (giiii-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL288 AIRFOIL (giiii-il) Reynolds number: 200,000 Max Cl/Cd: 61.13 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiii-il-200000.txt Download as CSV file: xf-giiii-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL288 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5755 0.09789 0.09436 -0.0128 1.0000 0.0399
-9.000 -0.5806 0.09255 0.08903 -0.0195 1.0000 0.0400
-8.750 -0.5858 0.08842 0.08484 -0.0227 1.0000 0.0401
-8.500 -0.5877 0.08433 0.08064 -0.0250 1.0000 0.0402
-8.000 -0.5873 0.07225 0.06860 -0.0264 1.0000 0.0416
-7.750 -0.5784 0.06936 0.06574 -0.0256 1.0000 0.0429
-7.500 -0.5713 0.06614 0.06249 -0.0259 1.0000 0.0444
-7.250 -0.5641 0.06250 0.05876 -0.0267 1.0000 0.0462
-7.000 -0.5558 0.05869 0.05481 -0.0274 1.0000 0.0482
-6.750 -0.5431 0.05722 0.05274 -0.0273 1.0000 0.0523
-6.500 -0.5326 0.05531 0.05047 -0.0259 1.0000 0.0527
-6.250 -0.5296 0.04710 0.04242 -0.0260 1.0000 0.0546
-6.000 -0.5174 0.04433 0.03967 -0.0249 1.0000 0.0562
-5.750 -0.5053 0.04197 0.03721 -0.0234 1.0000 0.0585
-5.500 -0.4928 0.03981 0.03484 -0.0215 1.0000 0.0626
-5.250 -0.4844 0.03736 0.03189 -0.0186 1.0000 0.0682
-5.000 -0.4722 0.03487 0.02947 -0.0171 1.0000 0.0707
-4.500 -0.4477 0.03136 0.02565 -0.0131 1.0000 0.0850
-4.250 -0.4375 0.01718 0.01188 -0.0091 1.0000 0.0883
-4.000 -0.4050 0.01472 0.00918 -0.0112 0.9961 0.1015
-3.750 -0.3718 0.01280 0.00707 -0.0132 0.9919 0.1192
-3.500 -0.3628 0.02205 0.01467 -0.0050 1.0000 0.0513
-3.250 -0.3307 0.02037 0.01272 -0.0058 0.9980 0.0515
-3.000 -0.2915 0.01917 0.01126 -0.0078 0.9947 0.0524
-2.750 -0.2544 0.01756 0.00948 -0.0095 0.9911 0.0529
-2.500 -0.2186 0.01566 0.00758 -0.0112 0.9878 0.0560
-2.250 -0.1780 0.01487 0.00684 -0.0140 0.9838 0.0625
-2.000 -0.1402 0.01422 0.00613 -0.0160 0.9771 0.0665
-1.750 -0.1003 0.01326 0.00529 -0.0189 0.9719 0.0768
-1.500 -0.0632 0.01267 0.00472 -0.0209 0.9657 0.0878
-1.250 -0.0280 0.01144 0.00421 -0.0231 0.9599 0.2591
-1.000 -0.0149 0.00960 0.00473 -0.0179 0.9562 0.8963
-0.750 0.0355 0.00993 0.00502 -0.0204 0.9563 0.9594
-0.500 0.1068 0.01003 0.00500 -0.0286 0.9584 0.9823
-0.250 0.1882 0.00982 0.00471 -0.0393 0.9612 1.0000
0.000 0.2259 0.00967 0.00452 -0.0416 0.9495 1.0000
0.250 0.2577 0.00954 0.00436 -0.0426 0.9363 1.0000
0.500 0.2837 0.00944 0.00423 -0.0423 0.9214 1.0000
0.750 0.3064 0.00935 0.00411 -0.0412 0.9058 1.0000
1.000 0.3280 0.00929 0.00402 -0.0398 0.8904 1.0000
1.250 0.3495 0.00923 0.00394 -0.0384 0.8750 1.0000
1.500 0.3710 0.00919 0.00388 -0.0370 0.8597 1.0000
1.750 0.3926 0.00917 0.00383 -0.0356 0.8441 1.0000
2.000 0.4145 0.00915 0.00380 -0.0342 0.8280 1.0000
2.250 0.4366 0.00913 0.00376 -0.0328 0.8110 1.0000
2.500 0.4580 0.00910 0.00370 -0.0311 0.7883 1.0000
2.750 0.4794 0.00907 0.00360 -0.0294 0.7611 1.0000
3.000 0.5017 0.00908 0.00357 -0.0279 0.7336 1.0000
3.250 0.5243 0.00913 0.00356 -0.0265 0.7036 1.0000
3.500 0.5466 0.00923 0.00356 -0.0251 0.6673 1.0000
3.750 0.5686 0.00940 0.00360 -0.0237 0.6230 1.0000
4.000 0.5899 0.00965 0.00369 -0.0222 0.5668 1.0000
4.250 0.6098 0.01008 0.00382 -0.0206 0.4959 1.0000
4.500 0.6289 0.01066 0.00407 -0.0190 0.4201 1.0000
4.750 0.6467 0.01145 0.00442 -0.0173 0.3241 1.0000
5.000 0.6612 0.01280 0.00503 -0.0155 0.1828 1.0000
5.250 0.6779 0.01412 0.00586 -0.0140 0.1129 1.0000
5.500 0.6971 0.01514 0.00672 -0.0127 0.0924 1.0000
5.750 0.7182 0.01595 0.00751 -0.0116 0.0805 1.0000
6.000 0.7393 0.01686 0.00844 -0.0105 0.0727 1.0000
6.250 0.7595 0.01801 0.00953 -0.0094 0.0658 1.0000
6.500 0.7824 0.01882 0.01045 -0.0085 0.0606 1.0000
6.750 0.8049 0.01981 0.01145 -0.0077 0.0562 1.0000
7.000 0.8266 0.02157 0.01322 -0.0069 0.0521 1.0000
7.250 0.8502 0.02249 0.01433 -0.0061 0.0485 1.0000
7.500 0.8734 0.02381 0.01577 -0.0053 0.0457 1.0000
7.750 0.8959 0.02546 0.01748 -0.0047 0.0433 1.0000
8.000 0.9162 0.02829 0.02057 -0.0038 0.0410 1.0000
8.250 0.9368 0.02988 0.02252 -0.0026 0.0392 1.0000
8.500 0.9550 0.03245 0.02550 -0.0013 0.0381 1.0000
8.750 0.9697 0.03561 0.02910 0.0004 0.0376 1.0000
9.000 0.9815 0.03887 0.03278 0.0021 0.0368 1.0000
9.250 0.9937 0.04129 0.03547 0.0035 0.0353 1.0000
9.500 1.0057 0.04368 0.03803 0.0046 0.0341 1.0000
9.750 0.9834 0.05222 0.04748 0.0083 0.0371 1.0000
10.000 0.9707 0.05783 0.05343 0.0102 0.0388 1.0000
10.250 0.9578 0.06287 0.05866 0.0114 0.0401 1.0000
10.500 0.8585 0.05495 0.05106 0.0206 0.0392 1.0000
10.750 0.8322 0.05994 0.05618 0.0205 0.0397 1.0000
11.000 0.8051 0.06574 0.06210 0.0190 0.0401 1.0000
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Polar data table (+)
Polar graphs
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