GIII BL207 AIRFOIL (giiih-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL207 AIRFOIL (giiih-il) Reynolds number: 100,000 Max Cl/Cd: 47.68 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiih-il-100000.txt Download as CSV file: xf-giiih-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL207 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5849 0.09626 0.09152 -0.0159 1.0000 0.0803
-8.500 -0.5972 0.09252 0.08775 -0.0214 1.0000 0.0807
-8.250 -0.6078 0.08954 0.08458 -0.0251 1.0000 0.0811
-8.000 -0.4817 0.07315 0.06874 -0.0214 1.0000 0.0994
-7.750 -0.4888 0.06885 0.06447 -0.0232 1.0000 0.1020
-7.500 -0.4997 0.06449 0.06009 -0.0252 1.0000 0.1051
-7.250 -0.5236 0.06073 0.05605 -0.0289 1.0000 0.1085
-7.000 -0.5107 0.05500 0.05050 -0.0273 1.0000 0.1119
-6.750 -0.5052 0.05131 0.04678 -0.0267 1.0000 0.1182
-6.500 -0.5493 0.05965 0.05456 -0.0254 1.0000 0.1183
-6.250 -0.5418 0.05596 0.05074 -0.0254 1.0000 0.1268
-6.000 -0.5334 0.05298 0.04755 -0.0249 1.0000 0.1391
-5.750 -0.5236 0.05015 0.04460 -0.0238 1.0000 0.1529
-5.500 -0.5130 0.04719 0.04162 -0.0223 1.0000 0.1685
-5.250 -0.5052 0.04498 0.03934 -0.0204 1.0000 0.1954
-5.000 -0.4820 0.02855 0.02364 -0.0158 1.0000 0.2137
-4.750 -0.4790 0.02618 0.02126 -0.0130 1.0000 0.2405
-4.250 -0.4169 0.02965 0.02134 -0.0129 1.0000 0.0797
-4.000 -0.3970 0.02686 0.01830 -0.0114 1.0000 0.0765
-3.750 -0.3761 0.02517 0.01622 -0.0098 1.0000 0.0786
-3.500 -0.3539 0.02360 0.01428 -0.0083 1.0000 0.0799
-3.250 -0.3306 0.02212 0.01249 -0.0071 1.0000 0.0809
-3.000 -0.3064 0.02014 0.01051 -0.0064 1.0000 0.0851
-2.750 -0.2839 0.01940 0.00961 -0.0054 1.0000 0.0946
-2.500 -0.2605 0.01802 0.00839 -0.0047 1.0000 0.1030
-2.250 -0.2381 0.01714 0.00760 -0.0039 1.0000 0.1182
-2.000 -0.2158 0.01634 0.00686 -0.0031 1.0000 0.1351
-1.750 -0.0354 0.01323 0.00643 -0.0238 1.0000 1.0000
-1.500 -0.0424 0.01325 0.00638 -0.0188 1.0000 1.0000
-1.250 -0.0534 0.01327 0.00636 -0.0133 1.0000 1.0000
-1.000 -0.0620 0.01328 0.00631 -0.0082 1.0000 1.0000
-0.750 -0.0635 0.01333 0.00626 -0.0042 1.0000 1.0000
-0.500 -0.0562 0.01344 0.00625 -0.0017 1.0000 1.0000
-0.250 -0.0429 0.01362 0.00631 -0.0002 1.0000 1.0000
0.000 -0.0148 0.01390 0.00648 -0.0015 0.9968 1.0000
0.250 0.0307 0.01426 0.00672 -0.0059 0.9884 1.0000
0.500 0.0788 0.01461 0.00699 -0.0108 0.9792 1.0000
0.750 0.1301 0.01492 0.00726 -0.0161 0.9697 1.0000
1.000 0.1741 0.01515 0.00749 -0.0200 0.9585 1.0000
1.250 0.2178 0.01537 0.00772 -0.0237 0.9479 1.0000
1.500 0.2675 0.01553 0.00794 -0.0284 0.9388 1.0000
1.750 0.3171 0.01561 0.00812 -0.0329 0.9286 1.0000
2.000 0.3596 0.01567 0.00828 -0.0359 0.9164 1.0000
2.250 0.4005 0.01569 0.00841 -0.0383 0.9038 1.0000
2.500 0.4384 0.01567 0.00855 -0.0399 0.8904 1.0000
2.750 0.4727 0.01562 0.00863 -0.0406 0.8759 1.0000
3.000 0.5037 0.01553 0.00867 -0.0404 0.8601 1.0000
3.250 0.5337 0.01524 0.00853 -0.0392 0.8420 1.0000
3.500 0.5550 0.01474 0.00810 -0.0357 0.8128 1.0000
3.750 0.5735 0.01429 0.00770 -0.0317 0.7787 1.0000
4.000 0.5938 0.01395 0.00740 -0.0285 0.7456 1.0000
4.250 0.6132 0.01368 0.00716 -0.0254 0.7038 1.0000
4.500 0.6324 0.01352 0.00701 -0.0224 0.6478 1.0000
4.750 0.6494 0.01362 0.00688 -0.0190 0.5516 1.0000
5.000 0.6532 0.01535 0.00712 -0.0141 0.2933 1.0000
5.250 0.6595 0.01808 0.00855 -0.0110 0.1376 1.0000
5.500 0.6763 0.01963 0.00988 -0.0091 0.1089 1.0000
5.750 0.6959 0.02119 0.01133 -0.0076 0.0946 1.0000
6.000 0.7177 0.02273 0.01287 -0.0065 0.0827 1.0000
6.250 0.7424 0.02503 0.01501 -0.0058 0.0761 1.0000
6.500 0.7681 0.02676 0.01705 -0.0049 0.0714 1.0000
6.750 0.7916 0.02880 0.01909 -0.0043 0.0649 1.0000
7.000 0.8152 0.03198 0.02259 -0.0034 0.0630 1.0000
7.250 0.8365 0.03485 0.02594 -0.0020 0.0625 1.0000
7.500 0.8550 0.03789 0.02955 -0.0003 0.0618 1.0000
7.750 0.8699 0.04090 0.03313 0.0015 0.0600 1.0000
8.000 0.8826 0.04503 0.03771 0.0032 0.0611 1.0000
8.250 0.8981 0.05072 0.04352 0.0039 0.0641 1.0000
9.500 0.6364 0.08884 0.08427 -0.0043 0.1787 1.0000
9.750 0.6402 0.09296 0.08840 -0.0039 0.1736 1.0000
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Polar data table (+)
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