GIII BL75 AIRFOIL (giiic-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL75 AIRFOIL (giiic-il) Reynolds number: 200,000 Max Cl/Cd: 51.48 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiic-il-200000-n5.txt Download as CSV file: xf-giiic-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL75 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6723 0.08583 0.08255 -0.0062 1.0000 0.0127
-10.000 -0.6880 0.07561 0.07236 -0.0151 1.0000 0.0124
-9.750 -0.7106 0.06613 0.06278 -0.0221 1.0000 0.0122
-9.500 -0.7348 0.05906 0.05553 -0.0237 1.0000 0.0120
-9.250 -0.7563 0.05264 0.04885 -0.0228 1.0000 0.0119
-9.000 -0.7711 0.04639 0.04220 -0.0212 1.0000 0.0120
-8.750 -0.7781 0.04087 0.03618 -0.0190 1.0000 0.0121
-8.500 -0.7772 0.03627 0.03103 -0.0167 1.0000 0.0124
-8.250 -0.7695 0.03260 0.02683 -0.0146 1.0000 0.0128
-8.000 -0.7556 0.02998 0.02373 -0.0129 1.0000 0.0134
-7.750 -0.7412 0.02746 0.02087 -0.0114 1.0000 0.0143
-7.500 -0.7221 0.02629 0.01960 -0.0105 1.0000 0.0153
-7.250 -0.7024 0.02486 0.01797 -0.0094 1.0000 0.0162
-7.000 -0.6823 0.02329 0.01615 -0.0082 1.0000 0.0170
-6.750 -0.6617 0.02187 0.01452 -0.0070 1.0000 0.0180
-6.500 -0.6412 0.02069 0.01313 -0.0058 1.0000 0.0191
-6.250 -0.6212 0.01995 0.01224 -0.0044 1.0000 0.0204
-6.000 -0.5971 0.01851 0.01076 -0.0043 0.9948 0.0225
-5.750 -0.5649 0.01754 0.00970 -0.0056 0.9850 0.0244
-5.500 -0.5330 0.01667 0.00872 -0.0068 0.9749 0.0267
-5.250 -0.5010 0.01600 0.00793 -0.0079 0.9642 0.0299
-5.000 -0.4712 0.01513 0.00701 -0.0086 0.9530 0.0345
-4.750 -0.4409 0.01457 0.00633 -0.0092 0.9425 0.0397
-4.500 -0.4118 0.01397 0.00573 -0.0097 0.9326 0.0498
-4.250 -0.3840 0.01345 0.00526 -0.0098 0.9229 0.0674
-4.000 -0.3580 0.01297 0.00487 -0.0097 0.9132 0.0964
-3.750 -0.3321 0.01256 0.00455 -0.0095 0.9047 0.1315
-3.500 -0.3073 0.01214 0.00427 -0.0090 0.8959 0.1715
-3.250 -0.2832 0.01173 0.00400 -0.0084 0.8876 0.2191
-3.000 -0.2608 0.01118 0.00373 -0.0076 0.8798 0.2954
-2.750 -0.2454 0.01011 0.00341 -0.0056 0.8710 0.4689
-2.500 -0.2297 0.00936 0.00341 -0.0028 0.8638 0.6645
-2.250 -0.2063 0.00919 0.00348 -0.0013 0.8560 0.7396
-2.000 -0.1807 0.00917 0.00350 -0.0002 0.8496 0.7835
-1.750 -0.1546 0.00919 0.00349 0.0005 0.8419 0.8113
-1.500 -0.1281 0.00922 0.00348 0.0012 0.8355 0.8332
-1.250 -0.1014 0.00927 0.00349 0.0018 0.8275 0.8519
-1.000 -0.0738 0.00934 0.00351 0.0023 0.8210 0.8693
-0.750 -0.0461 0.00944 0.00359 0.0028 0.8129 0.8888
-0.500 -0.0175 0.00961 0.00372 0.0034 0.8062 0.9093
-0.250 0.0123 0.00972 0.00381 0.0033 0.7980 0.9226
0.000 0.0443 0.00975 0.00378 0.0026 0.7906 0.9272
0.250 0.0728 0.00976 0.00373 0.0025 0.7813 0.9335
0.500 0.1035 0.00976 0.00368 0.0020 0.7685 0.9382
0.750 0.1347 0.00974 0.00360 0.0014 0.7527 0.9426
1.000 0.1624 0.00973 0.00353 0.0016 0.7373 0.9491
1.250 0.1954 0.00973 0.00348 0.0005 0.7219 0.9526
1.500 0.2278 0.00974 0.00346 -0.0004 0.7048 0.9567
1.750 0.2570 0.00976 0.00343 -0.0007 0.6880 0.9625
2.000 0.2911 0.00979 0.00342 -0.0020 0.6709 0.9656
2.250 0.3245 0.00983 0.00343 -0.0033 0.6531 0.9692
2.500 0.3548 0.00989 0.00346 -0.0038 0.6340 0.9743
2.750 0.3886 0.00996 0.00349 -0.0052 0.6118 0.9775
3.000 0.4213 0.01005 0.00355 -0.0063 0.5876 0.9813
3.250 0.4524 0.01018 0.00363 -0.0071 0.5608 0.9857
3.500 0.4858 0.01033 0.00371 -0.0085 0.5286 0.9887
3.750 0.5179 0.01054 0.00383 -0.0097 0.4901 0.9925
4.000 0.5497 0.01084 0.00399 -0.0108 0.4365 0.9960
4.250 0.5812 0.01129 0.00420 -0.0121 0.3698 0.9994
4.500 0.6041 0.01178 0.00447 -0.0117 0.3204 1.0000
4.750 0.6245 0.01229 0.00480 -0.0107 0.2802 1.0000
5.000 0.6449 0.01276 0.00515 -0.0097 0.2428 1.0000
5.250 0.6655 0.01317 0.00548 -0.0087 0.2156 1.0000
5.500 0.6859 0.01358 0.00581 -0.0076 0.1887 1.0000
5.750 0.7058 0.01403 0.00617 -0.0065 0.1588 1.0000
6.000 0.7250 0.01456 0.00656 -0.0052 0.1228 1.0000
6.250 0.7421 0.01536 0.00712 -0.0038 0.0756 1.0000
6.500 0.7589 0.01622 0.00781 -0.0022 0.0486 1.0000
6.750 0.7765 0.01699 0.00856 -0.0006 0.0365 1.0000
7.000 0.7946 0.01769 0.00931 0.0009 0.0296 1.0000
7.250 0.8116 0.01853 0.01022 0.0026 0.0258 1.0000
7.500 0.8294 0.01927 0.01109 0.0042 0.0234 1.0000
7.750 0.8469 0.02004 0.01194 0.0057 0.0208 1.0000
8.000 0.8603 0.02130 0.01327 0.0076 0.0184 1.0000
8.250 0.8777 0.02219 0.01429 0.0091 0.0174 1.0000
8.500 0.8940 0.02327 0.01550 0.0107 0.0163 1.0000
8.750 0.9099 0.02448 0.01683 0.0122 0.0154 1.0000
9.000 0.9261 0.02566 0.01812 0.0136 0.0144 1.0000
9.250 0.9421 0.02675 0.01929 0.0148 0.0134 1.0000
9.500 0.9543 0.02849 0.02112 0.0164 0.0123 1.0000
9.750 0.9683 0.03010 0.02292 0.0178 0.0117 1.0000
10.000 0.9815 0.03182 0.02487 0.0194 0.0113 1.0000
10.250 0.9927 0.03378 0.02711 0.0210 0.0109 1.0000
10.500 1.0010 0.03592 0.02951 0.0227 0.0106 1.0000
10.750 1.0048 0.03816 0.03202 0.0248 0.0103 1.0000
11.000 1.0047 0.04058 0.03470 0.0270 0.0101 1.0000
11.250 1.0015 0.04325 0.03763 0.0287 0.0099 1.0000
11.500 0.9953 0.04628 0.04092 0.0300 0.0098 1.0000
11.750 0.9864 0.04971 0.04461 0.0305 0.0097 1.0000
12.000 0.9749 0.05364 0.04878 0.0303 0.0096 1.0000
12.250 0.9614 0.05815 0.05353 0.0291 0.0096 1.0000
12.500 0.9453 0.06350 0.05910 0.0268 0.0096 1.0000
12.750 0.9264 0.06993 0.06575 0.0231 0.0096 1.0000
13.000 0.9044 0.07776 0.07379 0.0180 0.0097 1.0000
13.250 0.8796 0.08735 0.08357 0.0113 0.0099 1.0000
13.500 0.8509 0.09925 0.09564 0.0033 0.0101 1.0000
13.750 0.8153 0.11398 0.11046 -0.0052 0.0105 1.0000
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Polar data table (+)
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