GIII BL0 AIRFOIL (giiia-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL0 AIRFOIL (giiia-il) Reynolds number: 500,000 Max Cl/Cd: 69.08 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiia-il-500000.txt Download as CSV file: xf-giiia-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL0 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5994 0.08052 0.07847 -0.0213 1.0000 0.0160
-11.500 -0.6032 0.07574 0.07370 -0.0236 1.0000 0.0163
-11.250 -0.7656 0.06485 0.06250 -0.0294 1.0000 0.0135
-11.000 -0.9091 0.04392 0.04057 -0.0294 1.0000 0.0117
-10.750 -0.9295 0.04016 0.03649 -0.0249 1.0000 0.0116
-10.500 -0.9348 0.03743 0.03350 -0.0216 1.0000 0.0117
-10.250 -0.9284 0.03583 0.03177 -0.0194 1.0000 0.0120
-10.000 -0.9162 0.03485 0.03072 -0.0177 1.0000 0.0124
-9.750 -0.9066 0.03331 0.02902 -0.0156 1.0000 0.0128
-9.500 -0.8993 0.03113 0.02656 -0.0130 1.0000 0.0133
-9.250 -0.8912 0.02879 0.02391 -0.0103 1.0000 0.0136
-9.000 -0.8811 0.02661 0.02142 -0.0076 1.0000 0.0140
-8.750 -0.8682 0.02492 0.01947 -0.0051 1.0000 0.0143
-8.500 -0.8538 0.02369 0.01803 -0.0028 1.0000 0.0147
-8.250 -0.8394 0.02248 0.01663 -0.0004 1.0000 0.0150
-8.000 -0.8285 0.02004 0.01399 0.0024 1.0000 0.0158
-7.750 -0.8145 0.01923 0.01315 0.0048 1.0000 0.0165
-7.500 -0.8006 0.01865 0.01250 0.0073 1.0000 0.0172
-7.250 -0.7868 0.01819 0.01199 0.0098 1.0000 0.0182
-7.000 -0.7726 0.01770 0.01143 0.0123 1.0000 0.0192
-6.750 -0.7576 0.01728 0.01093 0.0147 1.0000 0.0199
-6.500 -0.7316 0.01570 0.00923 0.0147 0.9982 0.0214
-6.250 -0.6937 0.01495 0.00847 0.0122 0.9952 0.0234
-6.000 -0.6593 0.01446 0.00792 0.0105 0.9927 0.0257
-5.750 -0.6293 0.01368 0.00707 0.0098 0.9894 0.0282
-5.500 -0.5975 0.01303 0.00643 0.0087 0.9866 0.0318
-5.250 -0.5628 0.01267 0.00602 0.0070 0.9844 0.0354
-5.000 -0.5293 0.01199 0.00535 0.0055 0.9825 0.0435
-4.750 -0.5009 0.01150 0.00488 0.0053 0.9778 0.0533
-4.500 -0.4688 0.01100 0.00447 0.0041 0.9747 0.0732
-4.250 -0.4357 0.01043 0.00411 0.0026 0.9722 0.1166
-4.000 -0.4017 0.00996 0.00385 0.0010 0.9698 0.1643
-3.750 -0.3744 0.00959 0.00364 0.0009 0.9643 0.2042
-3.500 -0.3458 0.00915 0.00340 0.0005 0.9596 0.2550
-3.250 -0.3191 0.00840 0.00306 0.0003 0.9553 0.3588
-3.000 -0.3079 0.00733 0.00281 0.0035 0.9455 0.5623
-2.750 -0.2853 0.00694 0.00267 0.0048 0.9378 0.6382
-2.500 -0.2634 0.00666 0.00254 0.0065 0.9279 0.6881
-2.250 -0.2414 0.00642 0.00244 0.0081 0.9174 0.7319
-2.000 -0.2174 0.00625 0.00235 0.0094 0.9077 0.7672
-1.750 -0.1928 0.00612 0.00230 0.0105 0.8976 0.7987
-1.500 -0.1678 0.00606 0.00228 0.0115 0.8867 0.8261
-1.250 -0.1412 0.00604 0.00227 0.0122 0.8756 0.8470
-1.000 -0.1147 0.00604 0.00226 0.0129 0.8632 0.8649
-0.750 -0.0882 0.00607 0.00225 0.0136 0.8488 0.8802
-0.500 -0.0611 0.00613 0.00227 0.0141 0.8326 0.8935
-0.250 -0.0336 0.00621 0.00231 0.0146 0.8140 0.9049
0.000 -0.0069 0.00631 0.00234 0.0152 0.7928 0.9157
0.250 0.0207 0.00645 0.00240 0.0157 0.7644 0.9248
0.500 0.0500 0.00666 0.00245 0.0158 0.7236 0.9317
0.750 0.0760 0.00694 0.00255 0.0165 0.6848 0.9405
1.000 0.1093 0.00724 0.00269 0.0155 0.6507 0.9448
1.250 0.1429 0.00749 0.00279 0.0144 0.6202 0.9481
1.500 0.1730 0.00769 0.00287 0.0139 0.5924 0.9528
1.750 0.2030 0.00788 0.00295 0.0134 0.5645 0.9572
2.000 0.2402 0.00809 0.00303 0.0113 0.5333 0.9588
2.250 0.2760 0.00830 0.00311 0.0094 0.5016 0.9611
2.500 0.3094 0.00853 0.00320 0.0081 0.4645 0.9642
2.750 0.3343 0.00882 0.00330 0.0086 0.4125 0.9701
3.000 0.3689 0.00937 0.00344 0.0066 0.3178 0.9717
3.250 0.4028 0.00992 0.00365 0.0048 0.2496 0.9736
3.500 0.4370 0.01022 0.00384 0.0032 0.2288 0.9760
3.750 0.4697 0.01046 0.00402 0.0019 0.2179 0.9792
4.000 0.4983 0.01071 0.00424 0.0015 0.2103 0.9832
4.250 0.5347 0.01087 0.00440 -0.0006 0.2042 0.9847
4.500 0.5702 0.01104 0.00458 -0.0025 0.1992 0.9865
4.750 0.6041 0.01131 0.00483 -0.0041 0.1948 0.9888
5.000 0.6372 0.01150 0.00506 -0.0055 0.1916 0.9913
5.250 0.6695 0.01162 0.00520 -0.0067 0.1850 0.9938
5.500 0.7039 0.01181 0.00539 -0.0084 0.1772 0.9955
5.750 0.7389 0.01186 0.00547 -0.0103 0.1698 0.9973
6.000 0.7730 0.01202 0.00564 -0.0119 0.1621 0.9992
6.250 0.8019 0.01210 0.00573 -0.0125 0.1534 1.0000
6.500 0.8253 0.01216 0.00585 -0.0118 0.1437 1.0000
6.750 0.8483 0.01228 0.00593 -0.0111 0.1266 1.0000
7.000 0.8622 0.01369 0.00674 -0.0093 0.0349 1.0000
7.250 0.8804 0.01439 0.00743 -0.0077 0.0254 1.0000
7.500 0.8984 0.01503 0.00815 -0.0060 0.0218 1.0000
7.750 0.9164 0.01557 0.00877 -0.0044 0.0197 1.0000
8.000 0.9317 0.01635 0.00961 -0.0023 0.0179 1.0000
8.250 0.9441 0.01731 0.01068 0.0003 0.0167 1.0000
8.500 0.9600 0.01784 0.01128 0.0023 0.0158 1.0000
8.750 0.9744 0.01845 0.01196 0.0045 0.0148 1.0000
9.000 0.9872 0.01914 0.01270 0.0070 0.0140 1.0000
9.250 0.9971 0.02000 0.01362 0.0099 0.0134 1.0000
9.500 1.0014 0.02122 0.01494 0.0136 0.0128 1.0000
9.750 1.0012 0.02286 0.01668 0.0180 0.0124 1.0000
10.000 1.0114 0.02361 0.01752 0.0208 0.0122 1.0000
10.250 1.0199 0.02451 0.01852 0.0238 0.0119 1.0000
10.500 1.0270 0.02555 0.01966 0.0269 0.0116 1.0000
10.750 1.0328 0.02670 0.02091 0.0301 0.0114 1.0000
11.000 1.0354 0.02788 0.02220 0.0338 0.0112 1.0000
11.250 1.0386 0.02923 0.02366 0.0369 0.0109 1.0000
11.500 1.0426 0.03075 0.02530 0.0396 0.0108 1.0000
11.750 1.0466 0.03233 0.02700 0.0419 0.0105 1.0000
12.000 1.0505 0.03395 0.02875 0.0438 0.0103 1.0000
12.250 1.0533 0.03568 0.03059 0.0454 0.0100 1.0000
12.500 1.0551 0.03755 0.03257 0.0466 0.0098 1.0000
12.750 1.0555 0.03973 0.03485 0.0476 0.0096 1.0000
13.000 1.0537 0.04233 0.03756 0.0483 0.0094 1.0000
13.250 1.0489 0.04548 0.04086 0.0486 0.0093 1.0000
13.500 1.0418 0.04911 0.04466 0.0483 0.0093 1.0000
13.750 1.0330 0.05312 0.04884 0.0474 0.0092 1.0000
14.000 1.0226 0.05759 0.05349 0.0458 0.0092 1.0000
14.250 1.0112 0.06247 0.05854 0.0435 0.0092 1.0000
14.500 0.9985 0.06783 0.06407 0.0406 0.0092 1.0000
14.750 0.9845 0.07368 0.07009 0.0372 0.0093 1.0000
15.000 0.9691 0.08014 0.07671 0.0332 0.0093 1.0000
15.250 0.9510 0.08756 0.08432 0.0285 0.0094 1.0000
15.500 0.9261 0.09696 0.09393 0.0226 0.0096 1.0000
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