GIII BL145 AIRFOIL (giiif-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL145 AIRFOIL (giiif-il) Reynolds number: 100,000 Max Cl/Cd: 44.46 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiif-il-100000-n5.txt Download as CSV file: xf-giiif-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL145 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5633 0.09715 0.09233 -0.0064 1.0000 0.0298
-8.750 -0.5643 0.09225 0.08748 -0.0094 1.0000 0.0279
-8.500 -0.5683 0.08654 0.08182 -0.0141 1.0000 0.0262
-8.250 -0.5769 0.07833 0.07356 -0.0238 1.0000 0.0232
-8.000 -0.5757 0.07418 0.06936 -0.0245 1.0000 0.0224
-7.750 -0.5752 0.06961 0.06472 -0.0258 1.0000 0.0221
-7.500 -0.5727 0.06503 0.06004 -0.0268 1.0000 0.0218
-7.250 -0.5682 0.06046 0.05533 -0.0274 1.0000 0.0216
-7.000 -0.5619 0.05592 0.05060 -0.0276 1.0000 0.0214
-6.750 -0.5539 0.05142 0.04587 -0.0273 1.0000 0.0213
-6.500 -0.5444 0.04698 0.04115 -0.0265 1.0000 0.0212
-6.250 -0.5337 0.04264 0.03647 -0.0252 1.0000 0.0213
-6.000 -0.5210 0.03849 0.03184 -0.0235 1.0000 0.0223
-5.750 -0.5090 0.03474 0.02763 -0.0216 1.0000 0.0237
-5.500 -0.4948 0.03239 0.02504 -0.0201 1.0000 0.0251
-5.250 -0.4785 0.02965 0.02190 -0.0183 1.0000 0.0258
-5.000 -0.4606 0.02720 0.01900 -0.0165 1.0000 0.0268
-4.750 -0.4413 0.02504 0.01646 -0.0149 1.0000 0.0282
-4.500 -0.4210 0.02345 0.01452 -0.0133 1.0000 0.0316
-4.250 -0.4000 0.02192 0.01265 -0.0119 1.0000 0.0345
-4.000 -0.3799 0.02041 0.01107 -0.0106 1.0000 0.0371
-3.750 -0.3582 0.01933 0.00989 -0.0096 0.9994 0.0407
-3.500 -0.3240 0.01822 0.00866 -0.0111 0.9938 0.0490
-3.250 -0.2901 0.01732 0.00764 -0.0126 0.9876 0.0606
-3.000 -0.2570 0.01659 0.00695 -0.0141 0.9808 0.0793
-2.750 -0.2232 0.01593 0.00626 -0.0156 0.9747 0.1018
-2.500 -0.1902 0.01531 0.00574 -0.0171 0.9677 0.1337
-2.250 -0.1583 0.01454 0.00525 -0.0186 0.9609 0.2029
-2.000 -0.1409 0.01243 0.00526 -0.0163 0.9547 0.7349
-1.750 -0.1133 0.01242 0.00540 -0.0149 0.9481 0.8357
-1.500 -0.0793 0.01254 0.00546 -0.0150 0.9425 0.8884
-1.250 -0.0360 0.01270 0.00547 -0.0172 0.9396 0.9282
-1.000 0.0242 0.01288 0.00551 -0.0229 0.9405 0.9658
-0.750 0.0789 0.01284 0.00533 -0.0286 0.9384 0.9787
-0.500 0.1171 0.01277 0.00516 -0.0312 0.9297 0.9838
-0.250 0.1561 0.01270 0.00501 -0.0340 0.9221 0.9885
0.000 0.1942 0.01263 0.00490 -0.0365 0.9139 0.9937
0.250 0.2317 0.01257 0.00482 -0.0390 0.9053 0.9990
0.500 0.2604 0.01255 0.00477 -0.0395 0.8956 1.0000
0.750 0.2860 0.01253 0.00474 -0.0392 0.8839 1.0000
1.000 0.3096 0.01251 0.00471 -0.0384 0.8693 1.0000
1.250 0.3318 0.01250 0.00471 -0.0372 0.8531 1.0000
1.500 0.3543 0.01250 0.00471 -0.0361 0.8384 1.0000
1.750 0.3772 0.01254 0.00477 -0.0351 0.8259 1.0000
2.000 0.4004 0.01258 0.00484 -0.0341 0.8142 1.0000
2.250 0.4231 0.01265 0.00500 -0.0331 0.8014 1.0000
2.500 0.4459 0.01273 0.00514 -0.0320 0.7884 1.0000
2.750 0.4688 0.01281 0.00529 -0.0310 0.7748 1.0000
3.000 0.4919 0.01289 0.00546 -0.0299 0.7606 1.0000
3.250 0.5150 0.01297 0.00563 -0.0287 0.7454 1.0000
3.500 0.5366 0.01301 0.00580 -0.0271 0.7211 1.0000
3.750 0.5564 0.01294 0.00568 -0.0247 0.6751 1.0000
4.000 0.5751 0.01300 0.00555 -0.0220 0.6036 1.0000
4.250 0.5935 0.01335 0.00558 -0.0197 0.5004 1.0000
4.500 0.6076 0.01435 0.00584 -0.0171 0.3640 1.0000
4.750 0.6205 0.01584 0.00654 -0.0151 0.2020 1.0000
5.000 0.6353 0.01742 0.00744 -0.0135 0.0963 1.0000
5.250 0.6539 0.01858 0.00840 -0.0122 0.0662 1.0000
5.500 0.6732 0.01965 0.00950 -0.0108 0.0543 1.0000
5.750 0.6931 0.02067 0.01068 -0.0095 0.0478 1.0000
6.000 0.7113 0.02195 0.01197 -0.0082 0.0416 1.0000
6.250 0.7321 0.02302 0.01321 -0.0070 0.0367 1.0000
6.500 0.7525 0.02445 0.01478 -0.0058 0.0337 1.0000
6.750 0.7730 0.02646 0.01681 -0.0048 0.0311 1.0000
7.000 0.7957 0.02806 0.01868 -0.0039 0.0278 1.0000
7.250 0.8181 0.03008 0.02101 -0.0029 0.0254 1.0000
7.500 0.8391 0.03254 0.02381 -0.0018 0.0239 1.0000
7.750 0.8577 0.03514 0.02677 -0.0005 0.0227 1.0000
8.000 0.8730 0.03742 0.02929 0.0005 0.0209 1.0000
8.250 0.8829 0.04114 0.03340 0.0020 0.0194 1.0000
8.500 0.8928 0.04428 0.03709 0.0039 0.0186 1.0000
8.750 0.8976 0.04816 0.04146 0.0058 0.0183 1.0000
9.000 0.8979 0.05223 0.04597 0.0076 0.0182 1.0000
9.250 0.8936 0.05639 0.05049 0.0093 0.0181 1.0000
9.500 0.8849 0.06053 0.05494 0.0107 0.0181 1.0000
9.750 0.8709 0.06444 0.05907 0.0121 0.0181 1.0000
10.000 0.8545 0.06868 0.06349 0.0122 0.0182 1.0000
10.250 0.8372 0.07361 0.06857 0.0104 0.0183 1.0000
10.500 0.8199 0.07949 0.07457 0.0069 0.0184 1.0000
10.750 0.8037 0.08650 0.08166 0.0019 0.0186 1.0000
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Polar data table (+)
Polar graphs
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