GIII BL45 AIRFOIL (giiib-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL45 AIRFOIL (giiib-il) Reynolds number: 200,000 Max Cl/Cd: 52.63 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiib-il-200000.txt Download as CSV file: xf-giiib-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL45 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6055 0.12207 0.11855 0.0071 1.0000 0.0485
-11.000 -0.6075 0.11715 0.11366 0.0041 1.0000 0.0505
-7.750 -0.7185 0.04233 0.03731 -0.0161 1.0000 0.0386
-7.500 -0.7141 0.03813 0.03271 -0.0133 1.0000 0.0376
-7.250 -0.7079 0.03401 0.02813 -0.0100 1.0000 0.0365
-7.000 -0.7010 0.02942 0.02283 -0.0061 1.0000 0.0344
-6.750 -0.6866 0.02674 0.01974 -0.0035 1.0000 0.0343
-6.500 -0.6695 0.02479 0.01754 -0.0014 1.0000 0.0350
-6.250 -0.6516 0.02326 0.01582 0.0005 1.0000 0.0363
-6.000 -0.6340 0.02225 0.01464 0.0025 1.0000 0.0389
-5.750 -0.6160 0.02118 0.01336 0.0045 1.0000 0.0407
-5.500 -0.5973 0.01970 0.01171 0.0063 1.0000 0.0422
-5.250 -0.5802 0.01818 0.01022 0.0082 1.0000 0.0451
-5.000 -0.5636 0.01754 0.00955 0.0101 1.0000 0.0495
-4.750 -0.5465 0.01681 0.00874 0.0121 1.0000 0.0541
-4.500 -0.5309 0.01588 0.00787 0.0141 1.0000 0.0607
-4.250 -0.5141 0.01515 0.00715 0.0159 1.0000 0.0710
-4.000 -0.4960 0.01454 0.00661 0.0175 1.0000 0.0895
-3.750 -0.4619 0.01355 0.00598 0.0155 0.9958 0.1509
-3.500 -0.4273 0.01263 0.00555 0.0133 0.9904 0.2474
-3.250 -0.3998 0.01099 0.00510 0.0121 0.9846 0.4850
-3.000 -0.3737 0.01016 0.00525 0.0129 0.9783 0.7190
-2.750 -0.3386 0.01019 0.00551 0.0124 0.9726 0.8047
-2.500 -0.3000 0.01044 0.00574 0.0112 0.9678 0.8523
-2.250 -0.2640 0.01071 0.00596 0.0104 0.9609 0.8807
-2.000 -0.2193 0.01103 0.00619 0.0079 0.9571 0.9004
-1.750 -0.1745 0.01132 0.00637 0.0052 0.9528 0.9143
-1.500 -0.1305 0.01156 0.00652 0.0026 0.9468 0.9255
-1.250 -0.0750 0.01179 0.00667 -0.0024 0.9439 0.9325
-1.000 -0.0191 0.01199 0.00679 -0.0075 0.9411 0.9432
-0.750 0.0329 0.01217 0.00692 -0.0118 0.9351 0.9557
-0.500 0.0816 0.01204 0.00674 -0.0160 0.9270 0.9602
-0.250 0.1146 0.01187 0.00651 -0.0167 0.9114 0.9661
0.000 0.1451 0.01168 0.00626 -0.0169 0.8912 0.9721
0.250 0.1784 0.01149 0.00600 -0.0177 0.8721 0.9777
0.500 0.2094 0.01135 0.00580 -0.0182 0.8549 0.9839
0.750 0.2458 0.01115 0.00554 -0.0199 0.8370 0.9885
1.000 0.2802 0.01100 0.00536 -0.0213 0.8179 0.9942
1.250 0.3182 0.01080 0.00512 -0.0236 0.8002 0.9985
1.500 0.3455 0.01068 0.00496 -0.0236 0.7825 1.0000
1.750 0.3682 0.01059 0.00484 -0.0228 0.7631 1.0000
2.000 0.3912 0.01051 0.00472 -0.0220 0.7424 1.0000
2.250 0.4143 0.01045 0.00461 -0.0211 0.7222 1.0000
2.500 0.4378 0.01042 0.00455 -0.0204 0.7003 1.0000
2.750 0.4614 0.01043 0.00451 -0.0196 0.6779 1.0000
3.000 0.4849 0.01046 0.00448 -0.0188 0.6526 1.0000
3.250 0.5085 0.01053 0.00448 -0.0180 0.6246 1.0000
3.500 0.5319 0.01063 0.00451 -0.0172 0.5941 1.0000
3.750 0.5551 0.01077 0.00459 -0.0164 0.5578 1.0000
4.000 0.5777 0.01099 0.00467 -0.0155 0.5104 1.0000
4.250 0.5989 0.01138 0.00479 -0.0144 0.4386 1.0000
4.500 0.6190 0.01199 0.00502 -0.0133 0.3605 1.0000
4.750 0.6394 0.01259 0.00538 -0.0123 0.3185 1.0000
5.000 0.6603 0.01312 0.00578 -0.0113 0.2948 1.0000
5.250 0.6809 0.01361 0.00617 -0.0102 0.2753 1.0000
5.500 0.7015 0.01399 0.00652 -0.0092 0.2547 1.0000
5.750 0.7216 0.01438 0.00685 -0.0080 0.2363 1.0000
6.000 0.7416 0.01475 0.00721 -0.0068 0.2200 1.0000
6.250 0.7621 0.01501 0.00754 -0.0057 0.2035 1.0000
6.500 0.7826 0.01524 0.00784 -0.0045 0.1839 1.0000
6.750 0.8024 0.01552 0.00812 -0.0032 0.1522 1.0000
7.000 0.8111 0.01720 0.00909 -0.0004 0.0584 1.0000
7.250 0.8232 0.01845 0.01037 0.0022 0.0461 1.0000
7.500 0.8370 0.01944 0.01144 0.0046 0.0407 1.0000
7.750 0.8453 0.02101 0.01300 0.0077 0.0370 1.0000
8.000 0.8614 0.02183 0.01394 0.0097 0.0340 1.0000
8.250 0.8756 0.02295 0.01511 0.0118 0.0317 1.0000
8.500 0.8898 0.02429 0.01647 0.0139 0.0301 1.0000
8.750 0.9048 0.02628 0.01848 0.0158 0.0287 1.0000
9.000 0.9224 0.02937 0.02174 0.0171 0.0278 1.0000
9.250 0.9383 0.03054 0.02314 0.0190 0.0270 1.0000
9.500 0.9530 0.03189 0.02474 0.0209 0.0257 1.0000
9.750 0.9663 0.03383 0.02693 0.0227 0.0249 1.0000
10.000 0.9768 0.03630 0.02972 0.0248 0.0246 1.0000
10.250 0.9834 0.03908 0.03283 0.0271 0.0246 1.0000
10.500 0.9851 0.04216 0.03627 0.0297 0.0248 1.0000
10.750 0.9815 0.04547 0.03992 0.0324 0.0251 1.0000
11.000 0.9721 0.04879 0.04354 0.0353 0.0255 1.0000
11.250 0.9582 0.05215 0.04715 0.0380 0.0259 1.0000
11.500 0.9419 0.05590 0.05112 0.0395 0.0262 1.0000
11.750 0.9239 0.06015 0.05557 0.0398 0.0266 1.0000
12.000 0.9044 0.06506 0.06066 0.0390 0.0269 1.0000
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Polar data table (+)
Polar graphs
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