GIII BL167 AIRFOIL (giiig-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL167 AIRFOIL (giiig-il) Reynolds number: 100,000 Max Cl/Cd: 44.61 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiig-il-100000-n5.txt Download as CSV file: xf-giiig-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL167 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5676 0.09976 0.09487 -0.0067 1.0000 0.0282
-9.000 -0.5661 0.09552 0.09066 -0.0080 1.0000 0.0271
-8.750 -0.5663 0.09093 0.08611 -0.0106 1.0000 0.0262
-8.500 -0.5682 0.08597 0.08120 -0.0144 1.0000 0.0255
-8.250 -0.5724 0.08087 0.07613 -0.0187 1.0000 0.0249
-8.000 -0.5751 0.07596 0.07119 -0.0217 1.0000 0.0242
-7.750 -0.5755 0.07092 0.06609 -0.0242 1.0000 0.0236
-7.500 -0.5740 0.06585 0.06091 -0.0261 1.0000 0.0230
-7.250 -0.5703 0.06078 0.05567 -0.0272 1.0000 0.0225
-7.000 -0.5637 0.05620 0.05091 -0.0275 1.0000 0.0226
-6.750 -0.5543 0.05243 0.04693 -0.0273 1.0000 0.0237
-6.500 -0.5437 0.04854 0.04279 -0.0268 1.0000 0.0250
-6.250 -0.5324 0.04446 0.03838 -0.0257 1.0000 0.0257
-6.000 -0.5205 0.04044 0.03400 -0.0242 1.0000 0.0258
-5.750 -0.5075 0.03668 0.02982 -0.0223 1.0000 0.0260
-5.500 -0.4932 0.03321 0.02590 -0.0203 1.0000 0.0264
-5.250 -0.4770 0.03009 0.02228 -0.0182 1.0000 0.0271
-5.000 -0.4584 0.02777 0.01940 -0.0163 1.0000 0.0291
-4.750 -0.4408 0.02564 0.01697 -0.0148 1.0000 0.0315
-4.500 -0.4213 0.02397 0.01505 -0.0134 1.0000 0.0330
-4.250 -0.4008 0.02242 0.01326 -0.0120 1.0000 0.0348
-4.000 -0.3798 0.02102 0.01165 -0.0106 1.0000 0.0372
-3.750 -0.3587 0.02010 0.01048 -0.0093 0.9999 0.0413
-3.500 -0.3249 0.01883 0.00924 -0.0110 0.9947 0.0480
-3.250 -0.2912 0.01778 0.00802 -0.0122 0.9887 0.0547
-3.000 -0.2581 0.01698 0.00720 -0.0138 0.9823 0.0687
-2.750 -0.2243 0.01620 0.00643 -0.0154 0.9765 0.0845
-2.500 -0.1920 0.01560 0.00586 -0.0166 0.9692 0.1096
-2.250 -0.1583 0.01485 0.00534 -0.0183 0.9635 0.1615
-2.000 -0.1416 0.01249 0.00524 -0.0164 0.9566 0.7005
-1.750 -0.1132 0.01243 0.00540 -0.0151 0.9511 0.8266
-1.500 -0.0814 0.01255 0.00551 -0.0145 0.9448 0.8874
-1.250 -0.0332 0.01279 0.00562 -0.0173 0.9436 0.9411
-1.000 0.0355 0.01294 0.00558 -0.0249 0.9475 0.9755
-0.750 0.0781 0.01285 0.00538 -0.0284 0.9408 0.9801
-0.500 0.1170 0.01279 0.00520 -0.0312 0.9329 0.9855
-0.250 0.1577 0.01270 0.00504 -0.0343 0.9257 0.9898
0.000 0.1954 0.01264 0.00494 -0.0368 0.9168 0.9953
0.250 0.2335 0.01257 0.00484 -0.0393 0.9089 1.0000
0.500 0.2603 0.01255 0.00480 -0.0394 0.8978 1.0000
0.750 0.2854 0.01252 0.00475 -0.0390 0.8841 1.0000
1.000 0.3093 0.01248 0.00469 -0.0381 0.8685 1.0000
1.250 0.3318 0.01247 0.00469 -0.0370 0.8526 1.0000
1.500 0.3549 0.01249 0.00471 -0.0360 0.8396 1.0000
1.750 0.3781 0.01252 0.00476 -0.0350 0.8273 1.0000
2.000 0.4008 0.01257 0.00485 -0.0340 0.8143 1.0000
2.250 0.4236 0.01264 0.00499 -0.0330 0.8012 1.0000
2.500 0.4464 0.01271 0.00512 -0.0319 0.7878 1.0000
2.750 0.4695 0.01279 0.00526 -0.0308 0.7739 1.0000
3.000 0.4925 0.01286 0.00542 -0.0297 0.7591 1.0000
3.250 0.5157 0.01293 0.00561 -0.0286 0.7432 1.0000
3.500 0.5371 0.01294 0.00566 -0.0268 0.7153 1.0000
3.750 0.5567 0.01291 0.00559 -0.0244 0.6669 1.0000
4.000 0.5765 0.01300 0.00552 -0.0221 0.6049 1.0000
4.250 0.5951 0.01334 0.00555 -0.0198 0.5067 1.0000
4.500 0.6095 0.01430 0.00582 -0.0173 0.3729 1.0000
4.750 0.6243 0.01554 0.00641 -0.0154 0.2394 1.0000
5.000 0.6381 0.01718 0.00722 -0.0137 0.1090 1.0000
5.250 0.6565 0.01836 0.00818 -0.0124 0.0766 1.0000
5.500 0.6763 0.01935 0.00918 -0.0111 0.0605 1.0000
5.750 0.6955 0.02041 0.01027 -0.0099 0.0510 1.0000
6.000 0.7154 0.02145 0.01147 -0.0086 0.0463 1.0000
6.250 0.7350 0.02265 0.01282 -0.0073 0.0424 1.0000
6.500 0.7537 0.02421 0.01434 -0.0061 0.0381 1.0000
6.750 0.7762 0.02541 0.01577 -0.0051 0.0344 1.0000
7.000 0.7984 0.02712 0.01766 -0.0042 0.0320 1.0000
7.250 0.8199 0.02883 0.01950 -0.0033 0.0294 1.0000
7.500 0.8398 0.03111 0.02196 -0.0025 0.0265 1.0000
7.750 0.8603 0.03351 0.02480 -0.0012 0.0248 1.0000
8.000 0.8778 0.03651 0.02829 0.0002 0.0237 1.0000
8.250 0.8916 0.03984 0.03219 0.0019 0.0228 1.0000
8.500 0.9027 0.04288 0.03567 0.0035 0.0214 1.0000
8.750 0.9131 0.04520 0.03827 0.0048 0.0198 1.0000
9.000 0.9205 0.04767 0.04096 0.0060 0.0186 1.0000
9.250 0.9217 0.05123 0.04482 0.0075 0.0181 1.0000
9.500 0.9175 0.05526 0.04919 0.0092 0.0179 1.0000
9.750 0.9089 0.05932 0.05354 0.0108 0.0178 1.0000
10.000 0.8953 0.06308 0.05754 0.0124 0.0177 1.0000
10.250 0.8796 0.06708 0.06176 0.0128 0.0178 1.0000
10.500 0.8624 0.07176 0.06663 0.0116 0.0179 1.0000
10.750 0.8432 0.07772 0.07278 0.0083 0.0181 1.0000
11.000 0.8185 0.08703 0.08226 0.0013 0.0187 1.0000
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Polar data table (+)
Polar graphs
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