AG03 (flat aft bottom) (ag03-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG03 (flat aft bottom) (ag03-il) Reynolds number: 200,000 Max Cl/Cd: 60.57 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag03-il-200000.txt Download as CSV file: xf-ag03-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG03 (flat aft bottom)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5353 0.10285 0.09944 0.0043 1.0000 0.0276
-8.000 -0.5305 0.09893 0.09557 0.0008 1.0000 0.0277
-7.750 -0.5322 0.09233 0.08903 -0.0016 1.0000 0.0282
-7.500 -0.5273 0.08855 0.08526 0.0012 1.0000 0.0293
-7.250 -0.5191 0.08502 0.08174 0.0000 1.0000 0.0303
-7.000 -0.5096 0.08111 0.07785 -0.0031 1.0000 0.0314
-6.750 -0.4982 0.07698 0.07372 -0.0071 1.0000 0.0332
-6.500 -0.4833 0.07231 0.06902 -0.0129 1.0000 0.0359
-6.250 -0.4511 0.06666 0.06311 -0.0254 1.0000 0.0390
-6.000 -0.4393 0.05971 0.05604 -0.0293 1.0000 0.0400
-5.750 -0.4309 0.05675 0.05322 -0.0275 1.0000 0.0419
-5.500 -0.4135 0.05337 0.04978 -0.0287 1.0000 0.0442
-5.250 -0.3919 0.04937 0.04562 -0.0311 1.0000 0.0476
-5.000 -0.3634 0.04393 0.03959 -0.0351 1.0000 0.0528
-4.750 -0.3467 0.04056 0.03632 -0.0350 1.0000 0.0547
-4.500 -0.3259 0.03791 0.03356 -0.0351 1.0000 0.0582
-4.250 -0.3004 0.03432 0.02946 -0.0360 1.0000 0.0666
-4.000 -0.2797 0.03170 0.02685 -0.0357 1.0000 0.0695
-3.750 -0.2554 0.02928 0.02402 -0.0355 1.0000 0.0802
-3.500 -0.2198 0.02114 0.01458 -0.0328 1.0000 0.0283
-3.250 -0.1949 0.01867 0.01184 -0.0319 1.0000 0.0263
-3.000 -0.1694 0.01653 0.00937 -0.0310 1.0000 0.0253
-2.750 -0.1436 0.01492 0.00754 -0.0301 1.0000 0.0252
-2.500 -0.1181 0.01366 0.00616 -0.0292 1.0000 0.0262
-2.250 -0.0926 0.01234 0.00477 -0.0285 1.0000 0.0297
-2.000 -0.0665 0.01137 0.00391 -0.0281 1.0000 0.0580
-1.750 -0.0401 0.01026 0.00338 -0.0281 1.0000 0.1796
-1.500 -0.0149 0.00855 0.00318 -0.0286 1.0000 0.5573
-1.250 0.0150 0.00749 0.00312 -0.0276 1.0000 1.0000
-1.000 0.0389 0.00758 0.00302 -0.0270 1.0000 1.0000
-0.750 0.0627 0.00771 0.00301 -0.0266 1.0000 1.0000
-0.500 0.1120 0.00775 0.00289 -0.0312 0.9885 1.0000
-0.250 0.1607 0.00775 0.00276 -0.0356 0.9763 1.0000
0.000 0.2061 0.00772 0.00265 -0.0391 0.9616 1.0000
0.250 0.2475 0.00768 0.00253 -0.0416 0.9436 1.0000
0.500 0.2814 0.00765 0.00243 -0.0424 0.9197 1.0000
0.750 0.3102 0.00765 0.00236 -0.0419 0.8926 1.0000
1.000 0.3355 0.00769 0.00230 -0.0407 0.8632 1.0000
1.250 0.3599 0.00776 0.00225 -0.0394 0.8324 1.0000
1.500 0.3842 0.00788 0.00224 -0.0381 0.7998 1.0000
1.750 0.4087 0.00802 0.00226 -0.0369 0.7658 1.0000
2.000 0.4335 0.00820 0.00228 -0.0359 0.7314 1.0000
2.250 0.4586 0.00841 0.00233 -0.0349 0.6956 1.0000
2.500 0.4838 0.00863 0.00241 -0.0341 0.6588 1.0000
2.750 0.5091 0.00889 0.00250 -0.0333 0.6211 1.0000
3.000 0.5344 0.00916 0.00265 -0.0326 0.5820 1.0000
3.250 0.5598 0.00946 0.00279 -0.0320 0.5418 1.0000
3.500 0.5853 0.00978 0.00296 -0.0315 0.5011 1.0000
3.750 0.6106 0.01014 0.00316 -0.0310 0.4599 1.0000
4.000 0.6360 0.01052 0.00342 -0.0305 0.4195 1.0000
4.250 0.6614 0.01092 0.00369 -0.0301 0.3808 1.0000
4.500 0.6868 0.01135 0.00399 -0.0297 0.3439 1.0000
4.750 0.7122 0.01179 0.00432 -0.0293 0.3086 1.0000
5.000 0.7374 0.01227 0.00472 -0.0290 0.2762 1.0000
5.250 0.7628 0.01275 0.00513 -0.0287 0.2438 1.0000
5.500 0.7878 0.01328 0.00558 -0.0283 0.2131 1.0000
5.750 0.8126 0.01388 0.00609 -0.0280 0.1846 1.0000
6.000 0.8371 0.01455 0.00666 -0.0276 0.1567 1.0000
6.250 0.8615 0.01526 0.00737 -0.0272 0.1321 1.0000
6.500 0.8852 0.01613 0.00819 -0.0267 0.1125 1.0000
6.750 0.9092 0.01693 0.00900 -0.0262 0.0959 1.0000
7.000 0.9326 0.01790 0.01000 -0.0256 0.0836 1.0000
7.250 0.9555 0.01897 0.01111 -0.0249 0.0731 1.0000
7.500 0.9774 0.02025 0.01237 -0.0242 0.0637 1.0000
7.750 1.0010 0.02116 0.01350 -0.0236 0.0561 1.0000
8.000 1.0224 0.02265 0.01511 -0.0228 0.0489 1.0000
8.250 1.0441 0.02396 0.01650 -0.0220 0.0430 1.0000
8.500 1.0645 0.02581 0.01860 -0.0210 0.0375 1.0000
8.750 1.0851 0.02728 0.02023 -0.0202 0.0330 1.0000
9.000 1.1007 0.03041 0.02366 -0.0190 0.0293 1.0000
9.250 1.1194 0.03197 0.02557 -0.0179 0.0256 1.0000
9.500 1.1349 0.03417 0.02798 -0.0168 0.0231 1.0000
9.750 1.1389 0.03916 0.03336 -0.0152 0.0213 1.0000
10.000 1.1461 0.04177 0.03652 -0.0137 0.0195 1.0000
10.250 1.1490 0.04503 0.04021 -0.0122 0.0181 1.0000
10.500 1.1425 0.04927 0.04486 -0.0107 0.0176 1.0000
10.750 1.1283 0.05342 0.04935 -0.0091 0.0174 1.0000
11.000 1.1093 0.05797 0.05416 -0.0091 0.0174 1.0000
11.250 1.0886 0.06372 0.06016 -0.0119 0.0177 1.0000
11.500 1.0675 0.07101 0.06765 -0.0175 0.0181 1.0000
11.750 1.0461 0.07985 0.07661 -0.0249 0.0186 1.0000
12.000 1.0226 0.09007 0.08693 -0.0326 0.0197 1.0000
12.250 0.9395 0.12131 0.11821 -0.0506 0.0280 1.0000
12.500 0.9263 0.12973 0.12658 -0.0544 0.0287 1.0000
12.750 0.9169 0.13718 0.13399 -0.0575 0.0293 1.0000
13.000 0.9103 0.14379 0.14057 -0.0598 0.0299 1.0000
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Polar data table (+)
Polar graphs
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