AG46ct -02f rot. (ag46ct02r-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG46ct -02f rot. (ag46ct02r-il) Reynolds number: 500,000 Max Cl/Cd: 74.85 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag46ct02r-il-500000.txt Download as CSV file: xf-ag46ct02r-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AG46ct -02f rot.
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4729 0.08113 0.07910 0.0059 1.0000 0.0153
-7.750 -0.4736 0.07674 0.07472 0.0041 1.0000 0.0153
-7.500 -0.4748 0.07229 0.07028 0.0020 1.0000 0.0153
-7.250 -0.4762 0.06763 0.06565 -0.0011 1.0000 0.0153
-7.000 -0.4729 0.06202 0.06004 -0.0066 1.0000 0.0154
-6.750 -0.4799 0.05193 0.04994 -0.0140 1.0000 0.0158
-6.500 -0.4727 0.04591 0.04386 -0.0179 1.0000 0.0162
-6.250 -0.4613 0.04118 0.03905 -0.0205 1.0000 0.0165
-6.000 -0.4475 0.03661 0.03439 -0.0229 1.0000 0.0170
-5.750 -0.4316 0.03213 0.02980 -0.0251 1.0000 0.0175
-5.500 -0.4138 0.02758 0.02509 -0.0271 1.0000 0.0183
-5.250 -0.3944 0.02316 0.02047 -0.0287 1.0000 0.0193
-5.000 -0.3732 0.01905 0.01609 -0.0297 1.0000 0.0207
-4.750 -0.3452 0.01777 0.01447 -0.0292 1.0000 0.0231
-4.500 -0.3228 0.01507 0.01143 -0.0292 1.0000 0.0233
-4.250 -0.3159 0.02201 0.01757 -0.0309 1.0000 0.0253
-4.000 -0.2869 0.01580 0.01058 -0.0295 1.0000 0.0135
-3.750 -0.2599 0.01375 0.00821 -0.0289 1.0000 0.0137
-3.500 -0.2331 0.01251 0.00677 -0.0283 1.0000 0.0144
-3.250 -0.2063 0.01193 0.00608 -0.0278 1.0000 0.0152
-3.000 -0.1804 0.01033 0.00437 -0.0273 1.0000 0.0170
-2.750 -0.1538 0.00954 0.00353 -0.0268 1.0000 0.0181
-2.500 -0.1271 0.00898 0.00294 -0.0264 1.0000 0.0206
-2.250 -0.1001 0.00838 0.00227 -0.0260 1.0000 0.0271
-2.000 -0.0732 0.00785 0.00187 -0.0257 1.0000 0.0583
-1.750 -0.0465 0.00727 0.00168 -0.0257 1.0000 0.1543
-1.500 -0.0074 0.00664 0.00155 -0.0285 0.9878 0.2957
-1.250 0.0318 0.00568 0.00143 -0.0315 0.9599 0.5500
-1.000 0.0595 0.00477 0.00140 -0.0308 0.8976 0.8302
-0.750 0.0907 0.00468 0.00126 -0.0302 0.8148 1.0000
-0.500 0.1158 0.00492 0.00118 -0.0294 0.7644 1.0000
-0.250 0.1422 0.00511 0.00114 -0.0289 0.7353 1.0000
0.000 0.1691 0.00528 0.00113 -0.0285 0.7144 1.0000
0.250 0.1964 0.00541 0.00113 -0.0282 0.6960 1.0000
0.500 0.2239 0.00550 0.00112 -0.0280 0.6764 1.0000
0.750 0.2514 0.00558 0.00111 -0.0278 0.6549 1.0000
1.000 0.2788 0.00568 0.00110 -0.0276 0.6317 1.0000
1.250 0.3062 0.00580 0.00110 -0.0273 0.6076 1.0000
1.500 0.3336 0.00593 0.00112 -0.0271 0.5827 1.0000
1.750 0.3609 0.00607 0.00115 -0.0269 0.5569 1.0000
2.000 0.3883 0.00622 0.00120 -0.0267 0.5310 1.0000
2.250 0.4157 0.00638 0.00126 -0.0265 0.5035 1.0000
2.750 0.4703 0.00676 0.00142 -0.0262 0.4435 1.0000
3.000 0.4975 0.00698 0.00152 -0.0261 0.4111 1.0000
3.250 0.5246 0.00723 0.00165 -0.0259 0.3768 1.0000
3.500 0.5517 0.00750 0.00179 -0.0258 0.3421 1.0000
3.750 0.5787 0.00779 0.00198 -0.0257 0.3081 1.0000
4.000 0.6056 0.00812 0.00216 -0.0255 0.2721 1.0000
4.250 0.6325 0.00845 0.00238 -0.0254 0.2390 1.0000
4.750 0.6859 0.00919 0.00290 -0.0252 0.1784 1.0000
5.000 0.7126 0.00956 0.00318 -0.0251 0.1539 1.0000
5.250 0.7393 0.00993 0.00349 -0.0249 0.1330 1.0000
5.500 0.7659 0.01031 0.00382 -0.0248 0.1155 1.0000
5.750 0.7923 0.01072 0.00419 -0.0246 0.0993 1.0000
6.000 0.8186 0.01115 0.00459 -0.0244 0.0851 1.0000
6.250 0.8449 0.01158 0.00500 -0.0243 0.0719 1.0000
6.500 0.8709 0.01206 0.00546 -0.0240 0.0601 1.0000
6.750 0.8970 0.01251 0.00591 -0.0238 0.0502 1.0000
7.000 0.9229 0.01300 0.00647 -0.0236 0.0419 1.0000
7.250 0.9482 0.01368 0.00718 -0.0233 0.0344 1.0000
7.500 0.9721 0.01465 0.00819 -0.0228 0.0268 1.0000
7.750 0.9979 0.01512 0.00875 -0.0225 0.0238 1.0000
8.000 1.0221 0.01596 0.00964 -0.0221 0.0202 1.0000
8.250 1.0441 0.01733 0.01117 -0.0214 0.0176 1.0000
8.500 1.0688 0.01797 0.01194 -0.0210 0.0156 1.0000
8.750 1.0921 0.01886 0.01292 -0.0206 0.0140 1.0000
9.000 1.1106 0.02088 0.01512 -0.0197 0.0125 1.0000
9.250 1.1282 0.02312 0.01763 -0.0186 0.0117 1.0000
9.500 1.1492 0.02445 0.01916 -0.0179 0.0111 1.0000
9.750 1.1693 0.02579 0.02069 -0.0173 0.0102 1.0000
10.000 1.1896 0.02690 0.02193 -0.0167 0.0094 1.0000
10.250 1.2081 0.02823 0.02340 -0.0162 0.0087 1.0000
10.500 1.2218 0.03041 0.02578 -0.0153 0.0083 1.0000
10.750 1.2259 0.03413 0.02988 -0.0141 0.0079 1.0000
11.000 1.2187 0.03917 0.03535 -0.0127 0.0077 1.0000
11.250 1.2043 0.04403 0.04059 -0.0116 0.0076 1.0000
11.500 1.1860 0.04865 0.04548 -0.0120 0.0076 1.0000
11.750 1.1725 0.05417 0.05121 -0.0161 0.0076 1.0000
12.000 1.1591 0.06082 0.05806 -0.0217 0.0076 1.0000
12.250 1.1468 0.06795 0.06535 -0.0276 0.0076 1.0000
12.500 1.1348 0.07540 0.07294 -0.0334 0.0077 1.0000
12.750 1.1228 0.08299 0.08061 -0.0387 0.0077 1.0000
13.000 1.1094 0.09094 0.08865 -0.0439 0.0078 1.0000
13.250 1.0957 0.09903 0.09683 -0.0486 0.0079 1.0000
13.500 1.0781 0.10817 0.10606 -0.0537 0.0080 1.0000
13.750 0.7950 0.13033 0.12842 -0.0461 0.0120 1.0000
14.000 0.7784 0.13607 0.13415 -0.0480 0.0122 1.0000
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Polar data table (+)
Polar graphs
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