SARATOV AIRFOIL (saratov-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SARATOV AIRFOIL (saratov-il) Reynolds number: 500,000 Max Cl/Cd: 113.76 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-saratov-il-500000-n5.txt Download as CSV file: xf-saratov-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SARATOV AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.0529 0.09127 0.08652 -0.0975 0.5289 0.0233
-9.750 -0.0462 0.08874 0.08398 -0.0985 0.5274 0.0243
-9.250 -0.0522 0.08009 0.07535 -0.1019 0.5254 0.0270
-9.000 -0.0410 0.07865 0.07392 -0.1025 0.5242 0.0274
-8.750 -0.0304 0.07711 0.07237 -0.1030 0.5230 0.0278
-8.500 -0.0214 0.07534 0.07061 -0.1035 0.5218 0.0284
-8.250 -0.0142 0.07339 0.06866 -0.1040 0.5206 0.0291
-8.000 -0.1088 0.04800 0.04328 -0.1272 0.5223 0.0338
-7.750 -0.0911 0.04077 0.03586 -0.1389 0.5212 0.0346
-7.500 -0.0642 0.03618 0.03110 -0.1469 0.5198 0.0353
-7.250 -0.0341 0.03238 0.02710 -0.1537 0.5184 0.0361
-7.000 -0.0034 0.02947 0.02399 -0.1589 0.5168 0.0368
-6.750 0.0274 0.02703 0.02136 -0.1631 0.5153 0.0376
-6.500 0.0579 0.02501 0.01914 -0.1664 0.5139 0.0385
-6.250 0.0878 0.02339 0.01734 -0.1689 0.5124 0.0391
-6.000 0.1173 0.02204 0.01581 -0.1708 0.5111 0.0396
-5.750 0.1463 0.02094 0.01455 -0.1723 0.5099 0.0399
-5.500 0.1751 0.02012 0.01360 -0.1734 0.5087 0.0408
-5.250 0.2041 0.01932 0.01272 -0.1744 0.5079 0.0419
-5.000 0.2331 0.01851 0.01183 -0.1754 0.5072 0.0429
-4.750 0.2620 0.01775 0.01097 -0.1762 0.5064 0.0439
-4.500 0.2907 0.01709 0.01021 -0.1770 0.5055 0.0450
-4.250 0.3193 0.01645 0.00948 -0.1776 0.5047 0.0464
-4.000 0.3479 0.01588 0.00880 -0.1782 0.5039 0.0477
-3.750 0.3764 0.01539 0.00821 -0.1786 0.5031 0.0488
-3.500 0.4047 0.01495 0.00767 -0.1790 0.5023 0.0496
-3.250 0.4332 0.01450 0.00713 -0.1793 0.5014 0.0511
-3.000 0.4618 0.01391 0.00643 -0.1798 0.5007 0.0538
-2.750 0.4901 0.01342 0.00583 -0.1802 0.4999 0.0563
-2.500 0.5182 0.01305 0.00538 -0.1804 0.4991 0.0590
-2.250 0.5462 0.01277 0.00502 -0.1805 0.4984 0.0621
-2.000 0.5742 0.01246 0.00464 -0.1806 0.4977 0.0700
-1.750 0.6019 0.01193 0.00421 -0.1809 0.4971 0.1134
-1.500 0.6296 0.01190 0.00415 -0.1808 0.4964 0.1249
-1.250 0.6572 0.01190 0.00413 -0.1807 0.4958 0.1301
-1.000 0.6848 0.01193 0.00415 -0.1805 0.4951 0.1352
-0.750 0.7124 0.01196 0.00414 -0.1804 0.4945 0.1388
-0.500 0.7400 0.01200 0.00414 -0.1802 0.4939 0.1412
-0.250 0.7675 0.01205 0.00421 -0.1801 0.4933 0.1445
0.000 0.7951 0.01212 0.00427 -0.1799 0.4927 0.1468
0.250 0.8227 0.01219 0.00433 -0.1798 0.4921 0.1489
0.500 0.8502 0.01225 0.00438 -0.1796 0.4915 0.1513
0.750 0.8776 0.01224 0.00438 -0.1795 0.4906 0.1530
1.000 0.9048 0.01221 0.00436 -0.1792 0.4892 0.1540
1.250 0.9320 0.01222 0.00438 -0.1790 0.4878 0.1552
1.500 0.9593 0.01221 0.00440 -0.1788 0.4870 0.1577
1.750 0.9865 0.01222 0.00446 -0.1787 0.4861 0.1601
2.000 1.0136 0.01223 0.00449 -0.1784 0.4848 0.1613
2.250 1.0406 0.01224 0.00453 -0.1782 0.4833 0.1625
2.500 1.0675 0.01226 0.00458 -0.1780 0.4819 0.1639
2.750 1.0944 0.01229 0.00463 -0.1777 0.4805 0.1653
3.000 1.1212 0.01234 0.00469 -0.1775 0.4794 0.1668
3.250 1.1479 0.01239 0.00477 -0.1772 0.4779 0.1684
3.500 1.1744 0.01247 0.00485 -0.1769 0.4761 0.1699
3.750 1.2010 0.01254 0.00496 -0.1766 0.4747 0.1712
4.000 1.2276 0.01257 0.00507 -0.1763 0.4736 0.1729
4.250 1.2541 0.01260 0.00519 -0.1760 0.4723 0.1756
4.500 1.2805 0.01264 0.00531 -0.1757 0.4706 0.1788
4.750 1.3066 0.01266 0.00542 -0.1753 0.4682 0.1821
5.000 1.3324 0.01268 0.00550 -0.1749 0.4652 0.1853
5.250 1.3578 0.01272 0.00558 -0.1744 0.4622 0.1881
5.500 1.3829 0.01281 0.00571 -0.1739 0.4593 0.1925
5.750 1.4088 0.01281 0.00586 -0.1735 0.4552 0.1979
6.000 1.4332 0.01280 0.00592 -0.1728 0.4471 0.2037
6.250 1.4572 0.01281 0.00600 -0.1720 0.4338 0.2122
6.500 1.4548 0.01425 0.00676 -0.1669 0.3055 0.2186
6.750 1.4387 0.01685 0.00873 -0.1600 0.1813 0.2226
7.250 1.4579 0.01824 0.01016 -0.1537 0.1542 0.2530
7.500 1.4696 0.01891 0.01089 -0.1510 0.1467 0.2666
7.750 1.4796 0.01963 0.01162 -0.1482 0.1379 0.2774
8.000 1.4905 0.02031 0.01233 -0.1456 0.1303 0.2845
8.500 1.5075 0.02196 0.01398 -0.1402 0.1125 0.2971
8.750 1.5149 0.02292 0.01495 -0.1375 0.1019 0.3006
9.250 1.5209 0.02554 0.01751 -0.1317 0.0773 0.3082
9.500 1.5168 0.02756 0.01948 -0.1285 0.0612 0.3092
9.750 1.5087 0.03009 0.02198 -0.1255 0.0465 0.3102
10.000 1.5009 0.03292 0.02480 -0.1230 0.0344 0.3113
10.250 1.4948 0.03589 0.02778 -0.1210 0.0262 0.3126
10.500 1.4924 0.03869 0.03062 -0.1195 0.0219 0.3143
10.750 1.4915 0.04144 0.03343 -0.1182 0.0193 0.3169
11.000 1.4935 0.04394 0.03599 -0.1171 0.0178 0.3203
11.250 1.4953 0.04653 0.03864 -0.1162 0.0166 0.3211
11.500 1.4967 0.04919 0.04137 -0.1152 0.0155 0.3221
11.750 1.4983 0.05185 0.04410 -0.1143 0.0146 0.3234
12.000 1.5024 0.05427 0.04659 -0.1135 0.0140 0.3250
12.250 1.5069 0.05664 0.04903 -0.1128 0.0135 0.3267
12.500 1.5114 0.05902 0.05148 -0.1121 0.0129 0.3283
12.750 1.5162 0.06141 0.05394 -0.1115 0.0124 0.3306
13.000 1.5207 0.06385 0.05643 -0.1108 0.0119 0.3330
13.250 1.5247 0.06636 0.05901 -0.1102 0.0114 0.3347
13.500 1.5269 0.06914 0.06186 -0.1097 0.0109 0.3365
13.750 1.5338 0.07136 0.06414 -0.1092 0.0106 0.3385
14.000 1.5401 0.07367 0.06653 -0.1088 0.0103 0.3401
14.250 1.5461 0.07604 0.06897 -0.1084 0.0099 0.3413
14.500 1.5521 0.07844 0.07144 -0.1081 0.0096 0.3421
14.750 1.5581 0.08084 0.07391 -0.1078 0.0093 0.3428
15.000 1.5639 0.08331 0.07645 -0.1075 0.0090 0.3435
15.250 1.5691 0.08589 0.07909 -0.1073 0.0088 0.3440
15.500 1.5741 0.08849 0.08176 -0.1072 0.0085 0.3444
15.750 1.5781 0.09126 0.08460 -0.1071 0.0083 0.3448
16.000 1.5794 0.09446 0.08787 -0.1071 0.0081 0.3451
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