GIII BL288 AIRFOIL (giiii-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GIII BL288 AIRFOIL (giiii-il) Reynolds number: 200,000 Max Cl/Cd: 53.51 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiii-il-200000-n5.txt Download as CSV file: xf-giiii-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5791 0.08808 0.08454 -0.0110 1.0000 0.0222
-8.750 -0.5820 0.08262 0.07912 -0.0159 1.0000 0.0221
-8.500 -0.5873 0.07737 0.07385 -0.0204 1.0000 0.0219
-8.250 -0.5898 0.07235 0.06877 -0.0234 1.0000 0.0218
-8.000 -0.5896 0.06753 0.06387 -0.0255 1.0000 0.0216
-7.750 -0.5875 0.06284 0.05907 -0.0269 1.0000 0.0211
-7.500 -0.5836 0.05805 0.05413 -0.0278 1.0000 0.0206
-7.250 -0.5777 0.05328 0.04916 -0.0280 1.0000 0.0202
-7.000 -0.5699 0.04867 0.04432 -0.0277 1.0000 0.0200
-6.750 -0.5606 0.04437 0.03973 -0.0267 1.0000 0.0199
-6.500 -0.5502 0.04042 0.03548 -0.0253 1.0000 0.0199
-6.250 -0.5382 0.03708 0.03184 -0.0235 1.0000 0.0205
-6.000 -0.5254 0.03395 0.02836 -0.0214 1.0000 0.0215
-5.750 -0.5125 0.03099 0.02506 -0.0191 1.0000 0.0217
-5.500 -0.4987 0.02830 0.02202 -0.0169 1.0000 0.0217
-5.250 -0.4800 0.02574 0.01907 -0.0154 0.9989 0.0220
-5.000 -0.4482 0.02318 0.01605 -0.0164 0.9947 0.0224
-4.750 -0.4162 0.02132 0.01378 -0.0173 0.9899 0.0230
-4.500 -0.3836 0.01939 0.01163 -0.0186 0.9860 0.0240
-4.250 -0.3514 0.01861 0.01080 -0.0200 0.9807 0.0257
-4.000 -0.3174 0.01765 0.00973 -0.0214 0.9764 0.0273
-3.750 -0.2855 0.01657 0.00850 -0.0222 0.9707 0.0286
-3.500 -0.2528 0.01563 0.00746 -0.0232 0.9652 0.0302
-3.250 -0.2214 0.01495 0.00670 -0.0240 0.9586 0.0317
-3.000 -0.1910 0.01403 0.00583 -0.0248 0.9520 0.0354
-2.750 -0.1607 0.01354 0.00533 -0.0254 0.9446 0.0391
-2.500 -0.1300 0.01309 0.00483 -0.0261 0.9373 0.0425
-2.250 -0.1018 0.01253 0.00428 -0.0263 0.9285 0.0471
-2.000 -0.0718 0.01215 0.00384 -0.0267 0.9200 0.0514
-1.750 -0.0441 0.01187 0.00351 -0.0265 0.9088 0.0572
-1.500 -0.0171 0.01154 0.00318 -0.0263 0.8980 0.0670
-1.250 0.0097 0.01115 0.00291 -0.0260 0.8889 0.0999
-1.000 0.0156 0.00873 0.00286 -0.0221 0.8783 0.7200
-0.750 0.0368 0.00855 0.00297 -0.0198 0.8687 0.8201
-0.500 0.0619 0.00852 0.00300 -0.0183 0.8598 0.8670
-0.250 0.0892 0.00854 0.00300 -0.0175 0.8489 0.8970
0.000 0.1203 0.00861 0.00305 -0.0173 0.8370 0.9303
0.250 0.1537 0.00866 0.00305 -0.0180 0.8258 0.9499
0.500 0.1875 0.00866 0.00299 -0.0192 0.8148 0.9563
0.750 0.2189 0.00867 0.00293 -0.0198 0.8028 0.9640
1.000 0.2527 0.00868 0.00288 -0.0210 0.7893 0.9701
1.250 0.2856 0.00870 0.00286 -0.0221 0.7748 0.9769
1.500 0.3198 0.00872 0.00283 -0.0234 0.7595 0.9828
1.750 0.3541 0.00874 0.00282 -0.0248 0.7423 0.9884
2.000 0.3880 0.00877 0.00283 -0.0261 0.7231 0.9945
2.250 0.4224 0.00881 0.00281 -0.0276 0.7013 0.9997
2.500 0.4460 0.00890 0.00280 -0.0267 0.6716 1.0000
2.750 0.4683 0.00906 0.00279 -0.0255 0.6273 1.0000
3.000 0.4904 0.00928 0.00283 -0.0243 0.5753 1.0000
3.250 0.5121 0.00957 0.00290 -0.0231 0.5218 1.0000
3.500 0.5329 0.01000 0.00303 -0.0219 0.4593 1.0000
3.750 0.5533 0.01050 0.00324 -0.0206 0.3914 1.0000
4.000 0.5734 0.01108 0.00351 -0.0195 0.3228 1.0000
4.250 0.5937 0.01169 0.00382 -0.0184 0.2546 1.0000
4.500 0.6142 0.01235 0.00417 -0.0174 0.1914 1.0000
4.750 0.6352 0.01301 0.00458 -0.0164 0.1380 1.0000
5.000 0.6567 0.01364 0.00505 -0.0156 0.1022 1.0000
5.250 0.6786 0.01425 0.00554 -0.0148 0.0807 1.0000
5.500 0.7011 0.01480 0.00605 -0.0140 0.0678 1.0000
5.750 0.7242 0.01529 0.00659 -0.0133 0.0599 1.0000
6.000 0.7464 0.01590 0.00721 -0.0125 0.0535 1.0000
6.250 0.7694 0.01642 0.00780 -0.0118 0.0484 1.0000
6.500 0.7909 0.01716 0.00853 -0.0110 0.0442 1.0000
6.750 0.8133 0.01779 0.00924 -0.0102 0.0410 1.0000
7.000 0.8357 0.01841 0.00994 -0.0095 0.0377 1.0000
7.250 0.8573 0.01916 0.01077 -0.0087 0.0352 1.0000
7.500 0.8762 0.02039 0.01200 -0.0076 0.0328 1.0000
7.750 0.8985 0.02113 0.01290 -0.0068 0.0311 1.0000
8.000 0.9203 0.02194 0.01383 -0.0061 0.0289 1.0000
8.250 0.9414 0.02287 0.01487 -0.0053 0.0272 1.0000
8.500 0.9618 0.02391 0.01599 -0.0044 0.0259 1.0000
8.750 0.9800 0.02554 0.01769 -0.0034 0.0245 1.0000
9.000 1.0001 0.02678 0.01914 -0.0025 0.0233 1.0000
9.250 1.0198 0.02797 0.02057 -0.0016 0.0219 1.0000
9.500 1.0380 0.02942 0.02223 -0.0006 0.0208 1.0000
9.750 1.0550 0.03092 0.02396 0.0004 0.0199 1.0000
10.000 1.0712 0.03227 0.02546 0.0014 0.0190 1.0000
10.250 1.0856 0.03367 0.02696 0.0025 0.0182 1.0000
10.500 1.0954 0.03594 0.02950 0.0040 0.0174 1.0000
10.750 1.1035 0.03818 0.03213 0.0057 0.0166 1.0000
11.000 1.1062 0.04093 0.03524 0.0076 0.0160 1.0000
11.250 1.1027 0.04378 0.03842 0.0100 0.0156 1.0000
11.500 1.0943 0.04685 0.04178 0.0122 0.0153 1.0000
11.750 1.0822 0.05034 0.04555 0.0136 0.0150 1.0000
12.000 1.0667 0.05451 0.04998 0.0138 0.0149 1.0000
12.250 1.0479 0.05958 0.05531 0.0126 0.0148 1.0000
12.500 1.0245 0.06615 0.06213 0.0094 0.0148 1.0000
12.750 0.9939 0.07536 0.07159 0.0031 0.0150 1.0000
13.000 0.9486 0.09057 0.08704 -0.0083 0.0156 1.0000
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Polar data table (+)
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