GIII BL369 AIRFOIL (giiik-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL369 AIRFOIL (giiik-il) Reynolds number: 200,000 Max Cl/Cd: 51.9 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiik-il-200000-n5.txt Download as CSV file: xf-giiik-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL369 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5574 0.08968 0.08602 -0.0078 1.0000 0.0319
-8.500 -0.5629 0.08338 0.07974 -0.0165 1.0000 0.0326
-8.250 -0.5668 0.07792 0.07418 -0.0221 1.0000 0.0329
-7.750 -0.5086 0.05320 0.04949 -0.0298 1.0000 0.0258
-7.500 -0.5629 0.06157 0.05753 -0.0266 1.0000 0.0254
-7.250 -0.5557 0.05813 0.05404 -0.0268 1.0000 0.0247
-7.000 -0.5477 0.05412 0.04988 -0.0270 1.0000 0.0239
-6.750 -0.5389 0.04981 0.04537 -0.0269 1.0000 0.0232
-6.500 -0.5292 0.04538 0.04068 -0.0261 1.0000 0.0226
-6.250 -0.5186 0.04121 0.03621 -0.0248 1.0000 0.0222
-6.000 -0.5069 0.03754 0.03224 -0.0230 1.0000 0.0221
-5.750 -0.4932 0.03489 0.02935 -0.0213 1.0000 0.0223
-5.500 -0.4782 0.03282 0.02707 -0.0196 1.0000 0.0231
-5.250 -0.4633 0.03043 0.02440 -0.0176 1.0000 0.0238
-5.000 -0.4480 0.02798 0.02162 -0.0156 1.0000 0.0240
-4.750 -0.4245 0.02545 0.01873 -0.0150 0.9979 0.0241
-4.500 -0.3913 0.02295 0.01582 -0.0162 0.9935 0.0246
-4.250 -0.3570 0.02089 0.01336 -0.0174 0.9884 0.0253
-4.000 -0.3212 0.01933 0.01144 -0.0189 0.9830 0.0262
-3.750 -0.2853 0.01814 0.01024 -0.0209 0.9769 0.0277
-3.500 -0.2510 0.01741 0.00945 -0.0223 0.9690 0.0297
-3.250 -0.2160 0.01645 0.00836 -0.0237 0.9629 0.0314
-3.000 -0.1849 0.01571 0.00751 -0.0242 0.9544 0.0329
-2.750 -0.1530 0.01478 0.00659 -0.0251 0.9476 0.0353
-2.500 -0.1229 0.01415 0.00599 -0.0256 0.9384 0.0372
-2.250 -0.0928 0.01359 0.00543 -0.0260 0.9294 0.0390
-2.000 -0.0625 0.01318 0.00498 -0.0264 0.9201 0.0418
-1.750 -0.0348 0.01273 0.00453 -0.0262 0.9090 0.0434
-1.500 -0.0076 0.01221 0.00402 -0.0260 0.8981 0.0456
-1.250 0.0203 0.01190 0.00369 -0.0258 0.8873 0.0487
-1.000 0.0471 0.01167 0.00343 -0.0254 0.8747 0.0528
-0.750 0.0737 0.01143 0.00315 -0.0249 0.8621 0.0573
-0.500 0.1002 0.01122 0.00293 -0.0244 0.8489 0.0657
-0.250 0.1197 0.00983 0.00267 -0.0234 0.8349 0.3908
0.000 0.1294 0.00850 0.00286 -0.0187 0.8201 0.8098
0.250 0.1550 0.00843 0.00292 -0.0170 0.8040 0.8830
0.500 0.1873 0.00847 0.00294 -0.0171 0.7869 0.9248
0.750 0.2308 0.00857 0.00298 -0.0195 0.7686 0.9660
1.000 0.2727 0.00864 0.00292 -0.0221 0.7470 0.9814
1.250 0.3066 0.00869 0.00284 -0.0233 0.7208 0.9875
1.500 0.3408 0.00876 0.00278 -0.0246 0.6916 0.9936
1.750 0.3755 0.00883 0.00274 -0.0260 0.6613 0.9993
2.000 0.4004 0.00895 0.00271 -0.0254 0.6297 1.0000
2.250 0.4233 0.00914 0.00269 -0.0244 0.5890 1.0000
2.500 0.4459 0.00938 0.00272 -0.0234 0.5454 1.0000
2.750 0.4688 0.00963 0.00279 -0.0224 0.5090 1.0000
3.000 0.4920 0.00988 0.00289 -0.0216 0.4779 1.0000
3.250 0.5152 0.01015 0.00303 -0.0207 0.4455 1.0000
3.500 0.5382 0.01044 0.00318 -0.0198 0.4084 1.0000
3.750 0.5605 0.01080 0.00334 -0.0189 0.3578 1.0000
4.000 0.5819 0.01130 0.00356 -0.0179 0.2991 1.0000
4.250 0.6034 0.01187 0.00385 -0.0169 0.2430 1.0000
4.500 0.6253 0.01242 0.00416 -0.0161 0.1963 1.0000
4.750 0.6478 0.01293 0.00450 -0.0153 0.1603 1.0000
5.000 0.6707 0.01343 0.00485 -0.0146 0.1325 1.0000
5.250 0.6938 0.01392 0.00525 -0.0139 0.1121 1.0000
5.500 0.7170 0.01441 0.00567 -0.0132 0.0970 1.0000
5.750 0.7403 0.01490 0.00612 -0.0126 0.0852 1.0000
6.000 0.7639 0.01537 0.00659 -0.0120 0.0762 1.0000
6.250 0.7869 0.01592 0.00713 -0.0113 0.0694 1.0000
6.500 0.8103 0.01642 0.00768 -0.0106 0.0640 1.0000
6.750 0.8324 0.01710 0.00832 -0.0099 0.0595 1.0000
7.000 0.8557 0.01762 0.00894 -0.0092 0.0560 1.0000
7.250 0.8786 0.01819 0.00955 -0.0086 0.0526 1.0000
7.500 0.9001 0.01894 0.01030 -0.0078 0.0499 1.0000
7.750 0.9220 0.01968 0.01111 -0.0070 0.0479 1.0000
8.000 0.9443 0.02034 0.01188 -0.0063 0.0456 1.0000
8.250 0.9664 0.02101 0.01261 -0.0056 0.0432 1.0000
8.500 0.9875 0.02178 0.01341 -0.0049 0.0412 1.0000
8.750 1.0076 0.02278 0.01445 -0.0040 0.0394 1.0000
9.000 1.0289 0.02358 0.01541 -0.0033 0.0377 1.0000
9.250 1.0495 0.02445 0.01641 -0.0025 0.0360 1.0000
9.500 1.0697 0.02529 0.01733 -0.0017 0.0343 1.0000
9.750 1.0887 0.02622 0.01831 -0.0009 0.0329 1.0000
10.000 1.1061 0.02754 0.01972 0.0001 0.0315 1.0000
10.250 1.1243 0.02871 0.02111 0.0011 0.0304 1.0000
10.500 1.1413 0.03001 0.02260 0.0022 0.0293 1.0000
10.750 1.1571 0.03133 0.02409 0.0033 0.0282 1.0000
11.000 1.1718 0.03264 0.02555 0.0045 0.0273 1.0000
11.250 1.1853 0.03389 0.02691 0.0056 0.0265 1.0000
11.500 1.1965 0.03536 0.02846 0.0069 0.0258 1.0000
11.750 1.2033 0.03727 0.03056 0.0086 0.0250 1.0000
12.000 1.2071 0.03916 0.03274 0.0106 0.0244 1.0000
12.250 1.2075 0.04136 0.03520 0.0124 0.0238 1.0000
12.500 1.2052 0.04388 0.03797 0.0139 0.0233 1.0000
12.750 1.2004 0.04672 0.04106 0.0148 0.0229 1.0000
13.000 1.1933 0.04998 0.04456 0.0151 0.0226 1.0000
13.500 1.1717 0.05826 0.05330 0.0131 0.0221 1.0000
13.750 1.1561 0.06370 0.05896 0.0105 0.0219 1.0000
14.000 1.1357 0.07051 0.06601 0.0065 0.0219 1.0000
14.250 1.1067 0.07970 0.07543 0.0004 0.0220 1.0000
14.500 1.0544 0.09510 0.09114 -0.0102 0.0224 1.0000
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Polar data table (+)
Polar graphs
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