GIII BL288 AIRFOIL (giiii-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL288 AIRFOIL (giiii-il) Reynolds number: 500,000 Max Cl/Cd: 63.35 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiii-il-500000-n5.txt Download as CSV file: xf-giiii-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL288 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6174 0.08302 0.08079 -0.0093 1.0000 0.0098
-9.000 -0.6302 0.07514 0.07292 -0.0180 1.0000 0.0098
-8.750 -0.6389 0.06893 0.06664 -0.0226 1.0000 0.0098
-8.500 -0.6404 0.06353 0.06114 -0.0254 1.0000 0.0099
-8.250 -0.6384 0.05851 0.05600 -0.0271 1.0000 0.0101
-8.000 -0.6340 0.05357 0.05091 -0.0280 1.0000 0.0102
-7.750 -0.6280 0.04861 0.04575 -0.0281 1.0000 0.0105
-7.500 -0.6200 0.04386 0.04076 -0.0277 1.0000 0.0109
-7.250 -0.6137 0.03812 0.03469 -0.0262 1.0000 0.0115
-7.000 -0.6181 0.02862 0.02446 -0.0222 1.0000 0.0122
-6.750 -0.6087 0.02156 0.01654 -0.0198 0.9976 0.0126
-6.500 -0.5816 0.01870 0.01324 -0.0205 0.9932 0.0131
-6.250 -0.5512 0.01789 0.01233 -0.0216 0.9887 0.0135
-6.000 -0.5201 0.01711 0.01144 -0.0226 0.9843 0.0139
-5.750 -0.4903 0.01596 0.01010 -0.0233 0.9785 0.0143
-5.500 -0.4598 0.01491 0.00889 -0.0241 0.9730 0.0148
-5.250 -0.4299 0.01399 0.00785 -0.0246 0.9662 0.0154
-5.000 -0.4004 0.01319 0.00693 -0.0251 0.9588 0.0160
-4.750 -0.3710 0.01252 0.00615 -0.0255 0.9508 0.0166
-4.500 -0.3433 0.01198 0.00553 -0.0255 0.9412 0.0170
-4.250 -0.3168 0.01131 0.00481 -0.0253 0.9317 0.0179
-4.000 -0.2900 0.01098 0.00445 -0.0251 0.9218 0.0188
-3.750 -0.2635 0.01076 0.00420 -0.0249 0.9118 0.0202
-3.500 -0.2373 0.01048 0.00387 -0.0245 0.9017 0.0218
-3.250 -0.2112 0.01022 0.00354 -0.0240 0.8910 0.0229
-3.000 -0.1860 0.00981 0.00309 -0.0235 0.8796 0.0251
-2.750 -0.1598 0.00962 0.00285 -0.0231 0.8687 0.0272
-2.500 -0.1333 0.00944 0.00263 -0.0228 0.8584 0.0294
-2.250 -0.1066 0.00933 0.00247 -0.0225 0.8483 0.0314
-2.000 -0.0802 0.00908 0.00219 -0.0222 0.8393 0.0353
-1.750 -0.0534 0.00893 0.00203 -0.0220 0.8308 0.0389
-1.500 -0.0265 0.00881 0.00186 -0.0217 0.8206 0.0417
-1.250 0.0003 0.00869 0.00170 -0.0214 0.8087 0.0455
-1.000 0.0270 0.00856 0.00156 -0.0212 0.7962 0.0545
-0.750 0.0536 0.00838 0.00144 -0.0209 0.7852 0.0828
-0.500 0.0664 0.00625 0.00121 -0.0190 0.7746 0.6545
-0.250 0.0896 0.00598 0.00125 -0.0178 0.7631 0.7557
0.000 0.1151 0.00591 0.00124 -0.0171 0.7507 0.7917
0.250 0.1407 0.00586 0.00125 -0.0164 0.7375 0.8220
0.500 0.1663 0.00584 0.00126 -0.0157 0.7235 0.8488
0.750 0.1913 0.00582 0.00130 -0.0147 0.7087 0.8797
1.000 0.2170 0.00585 0.00133 -0.0140 0.6930 0.9033
1.250 0.2443 0.00591 0.00134 -0.0138 0.6763 0.9134
1.500 0.2719 0.00599 0.00137 -0.0136 0.6585 0.9238
2.000 0.3287 0.00622 0.00145 -0.0137 0.6051 0.9445
2.250 0.3571 0.00650 0.00150 -0.0139 0.5454 0.9541
2.500 0.3854 0.00684 0.00159 -0.0141 0.4841 0.9634
2.750 0.4163 0.00717 0.00171 -0.0150 0.4354 0.9704
3.000 0.4458 0.00766 0.00187 -0.0158 0.3559 0.9774
3.250 0.4760 0.00811 0.00206 -0.0167 0.2942 0.9839
3.500 0.5077 0.00849 0.00225 -0.0179 0.2444 0.9889
3.750 0.5389 0.00893 0.00246 -0.0190 0.1937 0.9940
4.000 0.5707 0.00940 0.00273 -0.0204 0.1422 0.9981
4.250 0.5970 0.00986 0.00299 -0.0205 0.1020 1.0000
4.500 0.6197 0.01023 0.00324 -0.0196 0.0805 1.0000
4.750 0.6429 0.01053 0.00349 -0.0189 0.0671 1.0000
5.000 0.6662 0.01084 0.00377 -0.0181 0.0562 1.0000
5.250 0.6899 0.01113 0.00404 -0.0175 0.0484 1.0000
5.500 0.7137 0.01146 0.00434 -0.0168 0.0423 1.0000
5.750 0.7378 0.01175 0.00465 -0.0162 0.0383 1.0000
6.000 0.7617 0.01212 0.00502 -0.0156 0.0345 1.0000
6.250 0.7857 0.01248 0.00541 -0.0150 0.0322 1.0000
6.500 0.8101 0.01281 0.00578 -0.0145 0.0303 1.0000
6.750 0.8343 0.01317 0.00617 -0.0140 0.0279 1.0000
7.000 0.8579 0.01363 0.00664 -0.0135 0.0254 1.0000
7.250 0.8812 0.01413 0.00720 -0.0129 0.0238 1.0000
7.500 0.9053 0.01453 0.00767 -0.0124 0.0226 1.0000
7.750 0.9290 0.01498 0.00817 -0.0119 0.0212 1.0000
8.000 0.9527 0.01543 0.00866 -0.0114 0.0197 1.0000
8.250 0.9751 0.01603 0.00929 -0.0107 0.0182 1.0000
8.500 0.9974 0.01668 0.01001 -0.0101 0.0173 1.0000
8.750 1.0202 0.01723 0.01064 -0.0095 0.0165 1.0000
9.000 1.0429 0.01777 0.01126 -0.0089 0.0156 1.0000
9.250 1.0657 0.01828 0.01184 -0.0084 0.0146 1.0000
9.500 1.0877 0.01887 0.01247 -0.0078 0.0138 1.0000
9.750 1.1066 0.01987 0.01355 -0.0068 0.0129 1.0000
10.000 1.1274 0.02061 0.01440 -0.0060 0.0125 1.0000
10.250 1.1477 0.02137 0.01528 -0.0053 0.0120 1.0000
10.500 1.1677 0.02213 0.01614 -0.0045 0.0113 1.0000
10.750 1.1877 0.02284 0.01696 -0.0037 0.0107 1.0000
11.000 1.2071 0.02356 0.01776 -0.0030 0.0102 1.0000
11.250 1.2241 0.02452 0.01880 -0.0019 0.0097 1.0000
11.500 1.2371 0.02589 0.02030 -0.0005 0.0092 1.0000
11.750 1.2519 0.02699 0.02156 0.0008 0.0090 1.0000
12.000 1.2644 0.02820 0.02295 0.0022 0.0087 1.0000
12.250 1.2736 0.02949 0.02439 0.0041 0.0083 1.0000
12.500 1.2810 0.03086 0.02592 0.0059 0.0081 1.0000
12.750 1.2869 0.03237 0.02757 0.0077 0.0078 1.0000
13.000 1.2920 0.03397 0.02933 0.0091 0.0076 1.0000
13.250 1.2961 0.03573 0.03123 0.0103 0.0074 1.0000
13.500 1.2991 0.03769 0.03332 0.0111 0.0072 1.0000
13.750 1.2998 0.04001 0.03578 0.0116 0.0070 1.0000
14.000 1.2968 0.04292 0.03883 0.0116 0.0068 1.0000
14.250 1.2893 0.04662 0.04268 0.0110 0.0067 1.0000
14.500 1.2768 0.05134 0.04759 0.0094 0.0066 1.0000
14.750 1.2653 0.05641 0.05285 0.0072 0.0065 1.0000
15.000 1.2510 0.06238 0.05901 0.0040 0.0065 1.0000
15.250 1.2314 0.06988 0.06669 -0.0005 0.0065 1.0000
15.500 1.2070 0.07884 0.07584 -0.0060 0.0065 1.0000
15.750 1.1772 0.08939 0.08657 -0.0123 0.0066 1.0000
16.000 1.1443 0.10102 0.09840 -0.0188 0.0068 1.0000
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