AG35 (ag35-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG35 (ag35-il) Reynolds number: 500,000 Max Cl/Cd: 82.18 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag35-il-500000-n5.txt Download as CSV file: xf-ag35-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG35
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5503 0.09282 0.09059 -0.0039 1.0000 0.0080
-10.750 -0.5565 0.08661 0.08442 -0.0076 1.0000 0.0081
-10.250 -0.6780 0.03142 0.02816 -0.0487 1.0000 0.0081
-10.000 -0.6695 0.02590 0.02192 -0.0488 1.0000 0.0083
-9.750 -0.6536 0.02275 0.01833 -0.0483 1.0000 0.0086
-9.500 -0.6325 0.02132 0.01670 -0.0478 1.0000 0.0088
-9.250 -0.6099 0.02048 0.01576 -0.0471 1.0000 0.0091
-9.000 -0.5874 0.01975 0.01492 -0.0464 1.0000 0.0095
-8.750 -0.5611 0.01878 0.01378 -0.0465 0.9977 0.0100
-8.500 -0.5303 0.01750 0.01226 -0.0474 0.9927 0.0105
-8.250 -0.4994 0.01627 0.01079 -0.0483 0.9864 0.0110
-8.000 -0.4684 0.01531 0.00963 -0.0491 0.9797 0.0114
-7.750 -0.4380 0.01423 0.00838 -0.0498 0.9722 0.0118
-7.500 -0.4079 0.01349 0.00756 -0.0503 0.9632 0.0124
-7.250 -0.3776 0.01297 0.00697 -0.0508 0.9534 0.0130
-7.000 -0.3488 0.01254 0.00646 -0.0509 0.9425 0.0138
-6.750 -0.3213 0.01209 0.00593 -0.0507 0.9303 0.0147
-6.500 -0.2946 0.01166 0.00538 -0.0502 0.9170 0.0153
-6.250 -0.2686 0.01110 0.00474 -0.0497 0.9037 0.0162
-6.000 -0.2423 0.01074 0.00431 -0.0492 0.8902 0.0173
-5.750 -0.2156 0.01045 0.00394 -0.0487 0.8772 0.0185
-5.500 -0.1888 0.01019 0.00359 -0.0483 0.8640 0.0200
-5.250 -0.1620 0.00990 0.00323 -0.0479 0.8492 0.0223
-5.000 -0.1349 0.00969 0.00296 -0.0475 0.8337 0.0251
-4.750 -0.1076 0.00950 0.00268 -0.0472 0.8182 0.0278
-4.500 -0.0804 0.00929 0.00243 -0.0469 0.8042 0.0334
-4.250 -0.0529 0.00913 0.00222 -0.0466 0.7902 0.0416
-4.000 -0.0255 0.00897 0.00203 -0.0464 0.7753 0.0541
-3.750 0.0020 0.00879 0.00187 -0.0462 0.7599 0.0765
-3.500 0.0295 0.00859 0.00173 -0.0461 0.7449 0.1103
-3.250 0.0569 0.00837 0.00161 -0.0460 0.7282 0.1582
-3.000 0.0843 0.00817 0.00151 -0.0460 0.7087 0.2138
-2.750 0.1116 0.00797 0.00143 -0.0459 0.6822 0.2758
-2.500 0.1381 0.00785 0.00134 -0.0457 0.6301 0.3433
-2.250 0.1646 0.00771 0.00130 -0.0455 0.6002 0.4281
-2.000 0.1910 0.00745 0.00130 -0.0454 0.5809 0.5409
-1.750 0.2166 0.00710 0.00132 -0.0450 0.5662 0.6763
-1.500 0.2394 0.00673 0.00137 -0.0436 0.5539 0.8165
-1.250 0.2626 0.00657 0.00142 -0.0420 0.5423 0.9274
-1.000 0.3021 0.00662 0.00141 -0.0444 0.5291 0.9837
-0.750 0.3363 0.00672 0.00142 -0.0458 0.5178 1.0000
-0.500 0.3637 0.00680 0.00144 -0.0457 0.5082 1.0000
-0.250 0.3911 0.00689 0.00146 -0.0456 0.4990 1.0000
0.000 0.4185 0.00700 0.00150 -0.0455 0.4892 1.0000
0.250 0.4462 0.00708 0.00154 -0.0454 0.4788 1.0000
0.500 0.4738 0.00717 0.00160 -0.0454 0.4682 1.0000
0.750 0.5014 0.00728 0.00165 -0.0453 0.4559 1.0000
1.000 0.5290 0.00739 0.00171 -0.0453 0.4423 1.0000
1.250 0.5565 0.00752 0.00179 -0.0453 0.4276 1.0000
1.500 0.5839 0.00766 0.00188 -0.0453 0.4109 1.0000
1.750 0.6112 0.00783 0.00198 -0.0452 0.3920 1.0000
2.000 0.6382 0.00804 0.00209 -0.0452 0.3705 1.0000
2.250 0.6651 0.00827 0.00224 -0.0452 0.3467 1.0000
2.500 0.6919 0.00853 0.00240 -0.0451 0.3216 1.0000
2.750 0.7186 0.00881 0.00258 -0.0451 0.2973 1.0000
3.000 0.7450 0.00911 0.00279 -0.0450 0.2728 1.0000
3.250 0.7716 0.00941 0.00300 -0.0450 0.2503 1.0000
3.500 0.7979 0.00973 0.00324 -0.0449 0.2291 1.0000
3.750 0.8243 0.01003 0.00349 -0.0449 0.2102 1.0000
4.000 0.8505 0.01036 0.00376 -0.0449 0.1917 1.0000
4.500 0.9027 0.01105 0.00434 -0.0447 0.1576 1.0000
4.750 0.9285 0.01142 0.00465 -0.0446 0.1400 1.0000
5.000 0.9538 0.01184 0.00501 -0.0445 0.1212 1.0000
5.250 0.9789 0.01229 0.00538 -0.0444 0.1023 1.0000
5.500 1.0037 0.01277 0.00579 -0.0442 0.0848 1.0000
5.750 1.0283 0.01328 0.00623 -0.0440 0.0702 1.0000
6.000 1.0527 0.01378 0.00670 -0.0438 0.0575 1.0000
6.250 1.0768 0.01430 0.00719 -0.0436 0.0464 1.0000
6.500 1.1007 0.01485 0.00770 -0.0433 0.0368 1.0000
6.750 1.1241 0.01544 0.00827 -0.0429 0.0285 1.0000
7.000 1.1473 0.01603 0.00887 -0.0426 0.0222 1.0000
7.250 1.1704 0.01661 0.00949 -0.0422 0.0182 1.0000
7.500 1.1928 0.01727 0.01017 -0.0417 0.0152 1.0000
7.750 1.2153 0.01788 0.01085 -0.0413 0.0133 1.0000
8.000 1.2362 0.01867 0.01167 -0.0407 0.0115 1.0000
8.250 1.2580 0.01930 0.01240 -0.0401 0.0105 1.0000
8.500 1.2788 0.02000 0.01318 -0.0395 0.0095 1.0000
8.750 1.2979 0.02086 0.01411 -0.0387 0.0086 1.0000
9.000 1.3162 0.02178 0.01511 -0.0378 0.0081 1.0000
9.250 1.3345 0.02262 0.01607 -0.0369 0.0077 1.0000
9.500 1.3515 0.02354 0.01710 -0.0359 0.0073 1.0000
9.750 1.3672 0.02451 0.01818 -0.0348 0.0069 1.0000
10.000 1.3814 0.02555 0.01933 -0.0335 0.0066 1.0000
10.250 1.3930 0.02668 0.02057 -0.0320 0.0064 1.0000
10.500 1.3993 0.02796 0.02195 -0.0297 0.0062 1.0000
10.750 1.4017 0.02958 0.02368 -0.0273 0.0060 1.0000
11.000 1.4014 0.03154 0.02577 -0.0253 0.0058 1.0000
11.250 1.4053 0.03332 0.02769 -0.0240 0.0057 1.0000
11.500 1.4077 0.03538 0.02990 -0.0230 0.0056 1.0000
11.750 1.4090 0.03774 0.03240 -0.0225 0.0055 1.0000
12.000 1.4088 0.04046 0.03527 -0.0224 0.0053 1.0000
12.250 1.4070 0.04356 0.03852 -0.0227 0.0052 1.0000
12.500 1.4041 0.04703 0.04214 -0.0234 0.0051 1.0000
12.750 1.3990 0.05104 0.04632 -0.0247 0.0050 1.0000
13.000 1.3931 0.05548 0.05091 -0.0265 0.0049 1.0000
13.250 1.3849 0.06035 0.05593 -0.0286 0.0048 1.0000
13.500 1.3745 0.06565 0.06137 -0.0308 0.0048 1.0000
13.750 1.3611 0.07143 0.06730 -0.0332 0.0048 1.0000
14.000 1.3465 0.07754 0.07355 -0.0358 0.0047 1.0000
14.250 1.3305 0.08406 0.08021 -0.0386 0.0047 1.0000
14.500 1.3137 0.09093 0.08722 -0.0416 0.0047 1.0000
14.750 1.2965 0.09811 0.09454 -0.0449 0.0047 1.0000
15.000 1.2791 0.10550 0.10205 -0.0482 0.0047 1.0000
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