GIII BL430 AIRFOIL (giiim-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL430 AIRFOIL (giiim-il) Reynolds number: 200,000 Max Cl/Cd: 56.08 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiim-il-200000.txt Download as CSV file: xf-giiim-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL430 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5345 0.09591 0.09226 0.0034 1.0000 0.0415
-8.250 -0.5404 0.09068 0.08707 -0.0058 1.0000 0.0420
-8.000 -0.5452 0.08534 0.08159 -0.0149 1.0000 0.0423
-7.750 -0.5446 0.08081 0.07690 -0.0188 1.0000 0.0425
-7.500 -0.5321 0.07619 0.07243 -0.0171 1.0000 0.0429
-7.250 -0.5219 0.07281 0.06908 -0.0166 1.0000 0.0434
-7.000 -0.5120 0.06945 0.06573 -0.0171 1.0000 0.0440
-6.750 -0.5013 0.06600 0.06223 -0.0183 1.0000 0.0448
-6.500 -0.4894 0.06246 0.05861 -0.0196 1.0000 0.0460
-6.250 -0.4754 0.05887 0.05489 -0.0211 1.0000 0.0478
-6.000 -0.4599 0.05589 0.05121 -0.0227 1.0000 0.0501
-5.750 -0.4461 0.05130 0.04678 -0.0227 1.0000 0.0507
-5.500 -0.4313 0.04837 0.04389 -0.0223 1.0000 0.0517
-5.250 -0.4155 0.04592 0.04141 -0.0218 1.0000 0.0534
-5.000 -0.3938 0.04658 0.04131 -0.0199 1.0000 0.0587
-4.750 -0.3824 0.04130 0.03613 -0.0194 1.0000 0.0597
-4.500 -0.3687 0.03850 0.03341 -0.0184 1.0000 0.0608
-4.250 -0.3554 0.03652 0.03141 -0.0168 1.0000 0.0625
-4.000 -0.3421 0.03494 0.02972 -0.0148 1.0000 0.0654
-3.750 -0.3284 0.03386 0.02814 -0.0121 1.0000 0.0705
-3.500 -0.3155 0.03138 0.02576 -0.0108 1.0000 0.0722
-3.250 -0.2841 0.02972 0.02399 -0.0123 0.9965 0.0780
-3.000 -0.2457 0.02734 0.02142 -0.0153 0.9908 0.0870
-2.750 -0.2050 0.02551 0.01935 -0.0183 0.9849 0.0995
-2.500 -0.1670 0.02377 0.01748 -0.0209 0.9776 0.1148
-2.250 -0.1265 0.02201 0.01570 -0.0241 0.9722 0.1350
-1.500 0.0009 0.01749 0.01014 -0.0276 0.9474 0.0792
-1.250 0.0375 0.01605 0.00862 -0.0285 0.9362 0.0750
-1.000 0.0716 0.01508 0.00752 -0.0288 0.9235 0.0725
-0.750 0.1007 0.01437 0.00682 -0.0284 0.9080 0.0740
-0.500 0.1263 0.01381 0.00627 -0.0272 0.8887 0.0761
-0.250 0.1501 0.01329 0.00573 -0.0255 0.8666 0.0771
0.000 0.1732 0.01285 0.00524 -0.0237 0.8432 0.0787
0.250 0.1966 0.01258 0.00490 -0.0220 0.8163 0.0816
0.500 0.2194 0.01202 0.00433 -0.0205 0.7922 0.0859
0.750 0.2439 0.01174 0.00401 -0.0194 0.7673 0.0905
1.000 0.2691 0.01156 0.00372 -0.0183 0.7435 0.0975
1.500 0.3038 0.00918 0.00342 -0.0136 0.6976 0.7860
1.750 0.3787 0.00901 0.00337 -0.0214 0.6634 1.0000
2.000 0.4029 0.00915 0.00332 -0.0204 0.6385 1.0000
2.250 0.4272 0.00931 0.00332 -0.0196 0.6142 1.0000
2.500 0.4515 0.00949 0.00334 -0.0187 0.5918 1.0000
2.750 0.4759 0.00966 0.00340 -0.0179 0.5684 1.0000
3.000 0.5002 0.00986 0.00347 -0.0170 0.5453 1.0000
3.250 0.5244 0.01006 0.00356 -0.0162 0.5208 1.0000
3.500 0.5485 0.01027 0.00367 -0.0153 0.4943 1.0000
3.750 0.5726 0.01048 0.00378 -0.0144 0.4633 1.0000
4.000 0.5962 0.01074 0.00389 -0.0136 0.4258 1.0000
4.250 0.6197 0.01105 0.00404 -0.0127 0.3705 1.0000
4.500 0.6414 0.01163 0.00424 -0.0117 0.3038 1.0000
4.750 0.6634 0.01230 0.00461 -0.0108 0.2563 1.0000
5.000 0.6859 0.01296 0.00505 -0.0101 0.2223 1.0000
5.250 0.7090 0.01358 0.00552 -0.0094 0.1954 1.0000
5.500 0.7321 0.01420 0.00599 -0.0087 0.1740 1.0000
5.750 0.7553 0.01484 0.00648 -0.0080 0.1569 1.0000
6.000 0.7789 0.01542 0.00701 -0.0074 0.1429 1.0000
6.250 0.8029 0.01595 0.00753 -0.0068 0.1313 1.0000
6.500 0.8264 0.01661 0.00816 -0.0061 0.1215 1.0000
6.750 0.8488 0.01744 0.00888 -0.0054 0.1132 1.0000
7.000 0.8730 0.01797 0.00949 -0.0048 0.1057 1.0000
7.250 0.8953 0.01893 0.01036 -0.0041 0.0993 1.0000
7.500 0.9192 0.01955 0.01106 -0.0035 0.0934 1.0000
7.750 0.9411 0.02074 0.01212 -0.0029 0.0880 1.0000
8.000 0.9649 0.02135 0.01290 -0.0022 0.0838 1.0000
8.250 0.9880 0.02214 0.01371 -0.0016 0.0798 1.0000
8.500 1.0100 0.02360 0.01510 -0.0011 0.0761 1.0000
8.750 1.0329 0.02435 0.01606 -0.0004 0.0730 1.0000
9.000 1.0553 0.02528 0.01708 0.0003 0.0700 1.0000
9.250 1.0776 0.02637 0.01816 0.0008 0.0676 1.0000
9.500 1.0985 0.02827 0.02015 0.0014 0.0653 1.0000
9.750 1.1188 0.02940 0.02154 0.0023 0.0632 1.0000
10.000 1.1388 0.03065 0.02297 0.0030 0.0611 1.0000
10.250 1.1583 0.03197 0.02441 0.0038 0.0594 1.0000
10.500 1.1779 0.03348 0.02597 0.0044 0.0579 1.0000
10.750 1.1937 0.03654 0.02916 0.0050 0.0565 1.0000
11.000 1.2053 0.03832 0.03134 0.0065 0.0555 1.0000
11.250 1.2140 0.04061 0.03400 0.0079 0.0543 1.0000
11.500 1.2201 0.04314 0.03686 0.0094 0.0532 1.0000
11.750 1.2226 0.04598 0.04002 0.0109 0.0525 1.0000
12.000 1.2203 0.04904 0.04336 0.0125 0.0519 1.0000
12.250 1.2108 0.05224 0.04683 0.0145 0.0515 1.0000
12.500 1.1921 0.05610 0.05095 0.0159 0.0514 1.0000
12.750 1.1611 0.06165 0.05682 0.0153 0.0516 1.0000
13.000 1.1110 0.07091 0.06643 0.0103 0.0523 1.0000
13.250 1.0292 0.08911 0.08499 -0.0037 0.0541 1.0000
13.500 0.9533 0.11131 0.10729 -0.0181 0.0562 1.0000
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Polar data table (+)
Polar graphs
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