GIII BL145 AIRFOIL (giiif-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GIII BL145 AIRFOIL (giiif-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.91 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiif-il-1000000.txt Download as CSV file: xf-giiif-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL145 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4674 0.10099 0.09948 -0.0059 1.0000 0.0082
-10.000 -0.4694 0.09637 0.09487 -0.0072 1.0000 0.0082
-6.500 -0.5974 0.02072 0.01700 -0.0178 0.9985 0.0071
-6.250 -0.5672 0.01805 0.01394 -0.0189 0.9954 0.0076
-6.000 -0.5361 0.01633 0.01194 -0.0199 0.9918 0.0079
-5.750 -0.5040 0.01526 0.01067 -0.0211 0.9872 0.0081
-5.500 -0.4742 0.01256 0.00759 -0.0218 0.9825 0.0087
-5.250 -0.4454 0.01145 0.00638 -0.0223 0.9737 0.0097
-5.000 -0.4150 0.01082 0.00567 -0.0230 0.9648 0.0105
-4.750 -0.3867 0.01029 0.00506 -0.0231 0.9530 0.0116
-4.500 -0.3609 0.00984 0.00452 -0.0226 0.9387 0.0124
-4.250 -0.3353 0.00957 0.00417 -0.0221 0.9241 0.0129
-4.000 -0.3124 0.00869 0.00311 -0.0210 0.9098 0.0150
-3.750 -0.2868 0.00844 0.00281 -0.0205 0.8972 0.0175
-3.500 -0.2608 0.00823 0.00251 -0.0201 0.8854 0.0194
-3.250 -0.2351 0.00788 0.00210 -0.0196 0.8740 0.0258
-3.000 -0.2088 0.00764 0.00188 -0.0194 0.8637 0.0402
-2.750 -0.1822 0.00749 0.00174 -0.0192 0.8545 0.0550
-2.500 -0.1553 0.00737 0.00160 -0.0190 0.8457 0.0672
-2.250 -0.1283 0.00724 0.00148 -0.0189 0.8374 0.0804
-2.000 -0.1015 0.00709 0.00136 -0.0188 0.8296 0.1003
-1.750 -0.0751 0.00684 0.00125 -0.0187 0.8211 0.1480
-1.500 -0.0510 0.00622 0.00110 -0.0183 0.8122 0.3029
-1.250 -0.0338 0.00487 0.00089 -0.0168 0.8024 0.6645
-1.000 -0.0084 0.00469 0.00088 -0.0162 0.7924 0.7279
-0.750 0.0177 0.00461 0.00087 -0.0158 0.7837 0.7657
-0.500 0.0445 0.00458 0.00085 -0.0155 0.7753 0.7882
-0.250 0.0712 0.00453 0.00084 -0.0152 0.7665 0.8101
0.000 0.0981 0.00452 0.00084 -0.0149 0.7580 0.8279
0.250 0.1249 0.00450 0.00084 -0.0146 0.7488 0.8446
0.500 0.1515 0.00447 0.00086 -0.0143 0.7402 0.8623
0.750 0.1779 0.00446 0.00087 -0.0139 0.7319 0.8799
1.000 0.2040 0.00445 0.00091 -0.0134 0.7227 0.9000
1.250 0.2304 0.00445 0.00094 -0.0130 0.7137 0.9152
1.500 0.2573 0.00448 0.00097 -0.0127 0.7043 0.9267
1.750 0.2845 0.00450 0.00101 -0.0125 0.6942 0.9373
2.000 0.3122 0.00453 0.00105 -0.0125 0.6824 0.9477
2.250 0.3397 0.00463 0.00108 -0.0124 0.6547 0.9579
2.500 0.3676 0.00479 0.00112 -0.0124 0.6179 0.9677
2.750 0.3995 0.00493 0.00121 -0.0134 0.5917 0.9738
3.000 0.4296 0.00512 0.00129 -0.0140 0.5537 0.9811
3.250 0.4601 0.00579 0.00146 -0.0151 0.4222 0.9855
3.500 0.4923 0.00636 0.00169 -0.0166 0.3352 0.9892
3.750 0.5231 0.00701 0.00195 -0.0179 0.2384 0.9933
4.000 0.5545 0.00784 0.00230 -0.0194 0.1232 0.9961
4.250 0.5872 0.00847 0.00264 -0.0211 0.0591 0.9988
4.500 0.6154 0.00887 0.00293 -0.0215 0.0352 1.0000
4.750 0.6373 0.00920 0.00324 -0.0205 0.0253 1.0000
5.000 0.6595 0.00954 0.00357 -0.0195 0.0204 1.0000
5.250 0.6811 0.01003 0.00414 -0.0183 0.0173 1.0000
5.500 0.7045 0.01030 0.00443 -0.0175 0.0160 1.0000
5.750 0.7277 0.01060 0.00474 -0.0168 0.0143 1.0000
6.000 0.7498 0.01111 0.00529 -0.0158 0.0126 1.0000
6.250 0.7680 0.01226 0.00661 -0.0141 0.0111 1.0000
6.500 0.7919 0.01264 0.00702 -0.0135 0.0107 1.0000
6.750 0.8152 0.01314 0.00757 -0.0128 0.0099 1.0000
7.000 0.8392 0.01354 0.00801 -0.0123 0.0090 1.0000
7.250 0.8634 0.01390 0.00838 -0.0119 0.0081 1.0000
7.500 0.8832 0.01508 0.00965 -0.0107 0.0074 1.0000
7.750 0.8986 0.01746 0.01229 -0.0088 0.0069 1.0000
8.000 0.9219 0.01811 0.01304 -0.0083 0.0067 1.0000
8.250 0.9442 0.01901 0.01406 -0.0076 0.0064 1.0000
8.500 0.9655 0.02014 0.01534 -0.0068 0.0061 1.0000
8.750 0.9860 0.02141 0.01678 -0.0059 0.0057 1.0000
9.000 1.0058 0.02269 0.01821 -0.0050 0.0053 1.0000
9.250 1.0241 0.02416 0.01987 -0.0040 0.0050 1.0000
9.500 1.0403 0.02592 0.02184 -0.0028 0.0048 1.0000
9.750 1.0510 0.02867 0.02490 -0.0010 0.0047 1.0000
10.000 0.9444 0.05179 0.04962 0.0097 0.0063 1.0000
10.250 0.9191 0.05633 0.05434 0.0115 0.0065 1.0000
10.500 0.8916 0.06177 0.05994 0.0103 0.0066 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GIII BL145 AIRFOIL (giiif-il)