GIII BL332 AIRFOIL (giiij-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL332 AIRFOIL (giiij-il) Reynolds number: 200,000 Max Cl/Cd: 52.43 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiij-il-200000-n5.txt Download as CSV file: xf-giiij-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL332 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4572 0.08540 0.08193 -0.0136 1.0000 0.0304
-9.000 -0.4613 0.08069 0.07725 -0.0154 1.0000 0.0304
-8.750 -0.4676 0.07559 0.07217 -0.0177 1.0000 0.0303
-8.500 -0.4795 0.06947 0.06608 -0.0217 1.0000 0.0298
-8.000 -0.5076 0.05812 0.05466 -0.0284 1.0000 0.0260
-7.500 -0.5841 0.05400 0.04967 -0.0284 1.0000 0.0212
-7.250 -0.5766 0.05011 0.04560 -0.0280 1.0000 0.0211
-7.000 -0.5676 0.04620 0.04147 -0.0273 1.0000 0.0210
-6.750 -0.5574 0.04242 0.03743 -0.0261 1.0000 0.0210
-6.500 -0.5479 0.03832 0.03293 -0.0243 1.0000 0.0215
-6.250 -0.5345 0.03656 0.03112 -0.0233 1.0000 0.0221
-6.000 -0.5194 0.03511 0.02958 -0.0220 1.0000 0.0227
-5.750 -0.5058 0.03256 0.02675 -0.0201 1.0000 0.0229
-5.500 -0.4924 0.02954 0.02336 -0.0177 1.0000 0.0227
-5.250 -0.4774 0.02720 0.02071 -0.0157 1.0000 0.0228
-5.000 -0.4536 0.02504 0.01824 -0.0153 0.9978 0.0230
-4.750 -0.4214 0.02301 0.01589 -0.0164 0.9938 0.0235
-4.500 -0.3892 0.02127 0.01385 -0.0175 0.9892 0.0243
-4.250 -0.3553 0.01973 0.01204 -0.0188 0.9856 0.0252
-4.000 -0.3225 0.01873 0.01080 -0.0197 0.9804 0.0271
-3.750 -0.2884 0.01743 0.00932 -0.0211 0.9763 0.0286
-3.500 -0.2559 0.01637 0.00824 -0.0222 0.9704 0.0299
-3.250 -0.2217 0.01554 0.00738 -0.0236 0.9641 0.0316
-3.000 -0.1894 0.01494 0.00675 -0.0245 0.9551 0.0343
-2.750 -0.1557 0.01439 0.00612 -0.0256 0.9472 0.0366
-2.500 -0.1267 0.01355 0.00529 -0.0259 0.9375 0.0385
-2.250 -0.0975 0.01303 0.00481 -0.0263 0.9289 0.0420
-2.000 -0.0680 0.01259 0.00436 -0.0266 0.9206 0.0447
-1.750 -0.0403 0.01224 0.00397 -0.0265 0.9108 0.0470
-1.500 -0.0119 0.01192 0.00360 -0.0265 0.9019 0.0504
-1.250 0.0153 0.01163 0.00330 -0.0262 0.8917 0.0561
-1.000 0.0423 0.01141 0.00305 -0.0259 0.8811 0.0626
-0.750 0.0683 0.01102 0.00283 -0.0254 0.8701 0.1039
-0.500 0.0731 0.00862 0.00286 -0.0210 0.8579 0.7626
-0.250 0.0953 0.00848 0.00294 -0.0186 0.8457 0.8501
0.000 0.1225 0.00848 0.00298 -0.0177 0.8335 0.8934
0.250 0.1541 0.00852 0.00300 -0.0177 0.8214 0.9254
0.500 0.1938 0.00860 0.00305 -0.0194 0.8087 0.9579
0.750 0.2293 0.00862 0.00299 -0.0208 0.7927 0.9688
1.000 0.2615 0.00864 0.00292 -0.0216 0.7753 0.9759
1.250 0.2960 0.00865 0.00286 -0.0229 0.7576 0.9814
1.500 0.3298 0.00869 0.00281 -0.0241 0.7385 0.9873
1.750 0.3640 0.00873 0.00279 -0.0255 0.7145 0.9932
2.000 0.3983 0.00880 0.00276 -0.0268 0.6871 0.9988
2.250 0.4239 0.00890 0.00275 -0.0264 0.6567 1.0000
2.500 0.4465 0.00907 0.00273 -0.0253 0.6119 1.0000
2.750 0.4683 0.00933 0.00274 -0.0241 0.5575 1.0000
3.000 0.4905 0.00962 0.00281 -0.0230 0.5107 1.0000
3.250 0.5128 0.00994 0.00294 -0.0220 0.4709 1.0000
3.500 0.5354 0.01025 0.00312 -0.0210 0.4311 1.0000
3.750 0.5573 0.01063 0.00330 -0.0200 0.3800 1.0000
4.000 0.5786 0.01110 0.00352 -0.0190 0.3237 1.0000
4.250 0.5998 0.01164 0.00380 -0.0180 0.2662 1.0000
4.500 0.6209 0.01224 0.00414 -0.0170 0.2096 1.0000
4.750 0.6422 0.01286 0.00451 -0.0162 0.1613 1.0000
5.000 0.6643 0.01343 0.00491 -0.0154 0.1261 1.0000
5.250 0.6867 0.01398 0.00534 -0.0146 0.1030 1.0000
5.500 0.7095 0.01450 0.00580 -0.0139 0.0875 1.0000
5.750 0.7323 0.01503 0.00629 -0.0132 0.0761 1.0000
6.000 0.7557 0.01550 0.00679 -0.0125 0.0676 1.0000
6.250 0.7785 0.01606 0.00734 -0.0118 0.0604 1.0000
6.500 0.8015 0.01659 0.00793 -0.0111 0.0547 1.0000
6.750 0.8235 0.01726 0.00860 -0.0104 0.0500 1.0000
7.000 0.8465 0.01780 0.00922 -0.0097 0.0457 1.0000
7.250 0.8685 0.01848 0.00991 -0.0090 0.0421 1.0000
7.500 0.8896 0.01930 0.01081 -0.0081 0.0397 1.0000
7.750 0.9114 0.02005 0.01165 -0.0073 0.0374 1.0000
8.000 0.9331 0.02078 0.01246 -0.0065 0.0351 1.0000
8.250 0.9540 0.02159 0.01330 -0.0058 0.0331 1.0000
8.500 0.9736 0.02270 0.01448 -0.0048 0.0314 1.0000
8.750 0.9943 0.02369 0.01563 -0.0039 0.0302 1.0000
9.000 1.0144 0.02478 0.01686 -0.0030 0.0290 1.0000
9.250 1.0342 0.02589 0.01810 -0.0021 0.0279 1.0000
9.500 1.0536 0.02691 0.01922 -0.0013 0.0267 1.0000
9.750 1.0719 0.02798 0.02038 -0.0004 0.0256 1.0000
10.000 1.0880 0.02966 0.02216 0.0006 0.0246 1.0000
10.250 1.1046 0.03117 0.02393 0.0018 0.0240 1.0000
10.500 1.1194 0.03292 0.02595 0.0030 0.0233 1.0000
10.750 1.1321 0.03474 0.02804 0.0043 0.0225 1.0000
11.000 1.1430 0.03648 0.03003 0.0058 0.0217 1.0000
11.250 1.1528 0.03806 0.03181 0.0072 0.0209 1.0000
11.500 1.1604 0.03951 0.03340 0.0088 0.0203 1.0000
11.750 1.1649 0.04111 0.03512 0.0106 0.0198 1.0000
12.000 1.1655 0.04318 0.03734 0.0123 0.0195 1.0000
12.250 1.1612 0.04590 0.04023 0.0138 0.0192 1.0000
12.500 1.1515 0.04931 0.04389 0.0148 0.0189 1.0000
12.750 1.1390 0.05321 0.04808 0.0148 0.0188 1.0000
13.000 1.1233 0.05791 0.05307 0.0137 0.0187 1.0000
13.250 1.1048 0.06355 0.05897 0.0113 0.0186 1.0000
13.500 1.0837 0.07035 0.06601 0.0073 0.0186 1.0000
13.750 1.0599 0.07851 0.07439 0.0018 0.0187 1.0000
14.000 1.0331 0.08823 0.08428 -0.0050 0.0188 1.0000
14.250 1.0016 0.09995 0.09615 -0.0128 0.0190 1.0000
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Polar data table (+)
Polar graphs
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