SARATOV AIRFOIL (saratov-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SARATOV AIRFOIL (saratov-il) Reynolds number: 500,000 Max Cl/Cd: 112.25 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-saratov-il-500000.txt Download as CSV file: xf-saratov-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.0116 0.09883 0.09437 -0.0974 0.5762 0.0362
-9.750 -0.0182 0.09592 0.09148 -0.1008 0.5742 0.0384
-9.500 -0.0137 0.09315 0.08869 -0.1021 0.5712 0.0385
-9.250 -0.0038 0.08954 0.08505 -0.1019 0.5680 0.0392
-9.000 0.0112 0.08799 0.08346 -0.1016 0.5650 0.0399
-8.750 0.0234 0.08636 0.08183 -0.1019 0.5629 0.0407
-8.500 0.0331 0.08444 0.07990 -0.1025 0.5606 0.0418
-8.250 0.0408 0.08232 0.07778 -0.1033 0.5587 0.0440
-8.000 0.0329 0.07993 0.07543 -0.1060 0.5575 0.0461
-7.750 0.0348 0.07758 0.07309 -0.1065 0.5559 0.0463
-7.500 0.0372 0.07377 0.06928 -0.1063 0.5542 0.0472
-7.250 0.0515 0.07250 0.06797 -0.1057 0.5523 0.0478
-7.000 0.0633 0.07107 0.06651 -0.1057 0.5505 0.0485
-6.750 0.0759 0.06951 0.06494 -0.1063 0.5490 0.0495
-6.500 0.0880 0.06767 0.06312 -0.1074 0.5479 0.0513
-6.250 0.0901 0.02569 0.02019 -0.1683 0.5487 0.0467
-6.000 0.1231 0.02177 0.01592 -0.1740 0.5474 0.0480
-5.750 0.1522 0.02044 0.01444 -0.1756 0.5459 0.0490
-5.500 0.1814 0.01930 0.01316 -0.1770 0.5444 0.0501
-5.250 0.2105 0.01827 0.01197 -0.1782 0.5428 0.0513
-5.000 0.2394 0.01741 0.01096 -0.1791 0.5412 0.0526
-4.750 0.2681 0.01670 0.01010 -0.1798 0.5398 0.0541
-4.500 0.2967 0.01612 0.00937 -0.1803 0.5384 0.0551
-4.250 0.3251 0.01559 0.00869 -0.1807 0.5372 0.0562
-4.000 0.3531 0.01519 0.00820 -0.1808 0.5360 0.0585
-3.750 0.3815 0.01485 0.00778 -0.1811 0.5347 0.0607
-3.500 0.4101 0.01454 0.00737 -0.1814 0.5334 0.0631
-3.250 0.4386 0.01420 0.00693 -0.1817 0.5326 0.0656
-3.000 0.4672 0.01381 0.00647 -0.1819 0.5319 0.0693
-2.750 0.4958 0.01328 0.00588 -0.1823 0.5312 0.0748
-2.500 0.5243 0.01268 0.00525 -0.1827 0.5304 0.0886
-2.250 0.5524 0.01242 0.00508 -0.1829 0.5296 0.1290
-2.000 0.5807 0.01266 0.00530 -0.1828 0.5289 0.1397
-1.750 0.6086 0.01290 0.00559 -0.1826 0.5281 0.1454
-1.500 0.6366 0.01318 0.00589 -0.1824 0.5273 0.1505
-1.250 0.6647 0.01334 0.00600 -0.1823 0.5266 0.1538
-1.000 0.6925 0.01331 0.00593 -0.1823 0.5259 0.1571
-0.750 0.7202 0.01348 0.00615 -0.1821 0.5253 0.1604
-0.500 0.7480 0.01362 0.00631 -0.1820 0.5246 0.1636
-0.250 0.7759 0.01364 0.00630 -0.1820 0.5240 0.1658
0.000 0.8038 0.01368 0.00630 -0.1819 0.5234 0.1680
0.250 0.8318 0.01378 0.00636 -0.1818 0.5228 0.1698
0.500 0.8595 0.01362 0.00616 -0.1819 0.5223 0.1723
0.750 0.8872 0.01362 0.00618 -0.1818 0.5214 0.1748
1.000 0.9147 0.01368 0.00624 -0.1817 0.5198 0.1772
1.250 0.9424 0.01382 0.00634 -0.1816 0.5178 0.1799
1.500 0.9701 0.01401 0.00651 -0.1816 0.5164 0.1817
1.750 0.9975 0.01396 0.00647 -0.1815 0.5158 0.1829
2.000 1.0248 0.01390 0.00644 -0.1813 0.5149 0.1840
2.250 1.0518 0.01387 0.00642 -0.1811 0.5138 0.1850
2.500 1.0789 0.01387 0.00645 -0.1809 0.5126 0.1859
2.750 1.1059 0.01379 0.00640 -0.1807 0.5113 0.1877
3.000 1.1329 0.01377 0.00644 -0.1805 0.5102 0.1899
3.250 1.1599 0.01378 0.00650 -0.1803 0.5088 0.1920
3.500 1.1868 0.01380 0.00655 -0.1801 0.5072 0.1943
3.750 1.2138 0.01384 0.00663 -0.1799 0.5058 0.1969
4.000 1.2409 0.01390 0.00672 -0.1797 0.5046 0.1995
4.250 1.2681 0.01399 0.00682 -0.1795 0.5033 0.2018
4.500 1.2953 0.01409 0.00697 -0.1794 0.5015 0.2062
4.750 1.3220 0.01431 0.00725 -0.1793 0.4995 0.2111
5.000 1.3474 0.01424 0.00729 -0.1787 0.4978 0.2160
5.250 1.3729 0.01420 0.00737 -0.1782 0.4956 0.2221
5.500 1.3986 0.01419 0.00748 -0.1778 0.4932 0.2305
5.750 1.4238 0.01407 0.00745 -0.1772 0.4892 0.2425
6.000 1.4496 0.01415 0.00753 -0.1766 0.4835 0.2595
6.250 1.4721 0.01406 0.00765 -0.1754 0.4787 0.2737
6.750 1.5180 0.01401 0.00770 -0.1732 0.4654 0.2953
7.000 1.5395 0.01390 0.00765 -0.1718 0.4550 0.3064
7.250 1.5602 0.01390 0.00773 -0.1703 0.4384 0.3087
7.500 1.5537 0.01519 0.00839 -0.1643 0.3155 0.3107
7.750 1.5235 0.01794 0.01051 -0.1548 0.1994 0.3113
8.000 1.5186 0.01931 0.01172 -0.1495 0.1706 0.3145
8.250 1.5225 0.02031 0.01267 -0.1458 0.1583 0.3210
8.500 1.5305 0.02114 0.01356 -0.1429 0.1503 0.3228
8.750 1.5353 0.02217 0.01461 -0.1397 0.1423 0.3251
9.000 1.5438 0.02307 0.01556 -0.1371 0.1352 0.3290
9.250 1.5483 0.02425 0.01673 -0.1342 0.1268 0.3348
9.500 1.5551 0.02534 0.01787 -0.1318 0.1177 0.3365
9.750 1.5572 0.02682 0.01936 -0.1291 0.1057 0.3387
10.000 1.5525 0.02894 0.02140 -0.1261 0.0859 0.3410
10.250 1.5376 0.03216 0.02450 -0.1228 0.0612 0.3428
10.500 1.5199 0.03610 0.02835 -0.1201 0.0423 0.3446
10.750 1.5086 0.03984 0.03207 -0.1182 0.0333 0.3479
11.000 1.5031 0.04306 0.03535 -0.1168 0.0292 0.3491
11.250 1.5003 0.04611 0.03847 -0.1156 0.0267 0.3511
11.500 1.5005 0.04888 0.04132 -0.1146 0.0251 0.3543
11.750 1.4995 0.05184 0.04433 -0.1137 0.0236 0.3576
12.000 1.4962 0.05510 0.04764 -0.1127 0.0223 0.3610
12.250 1.4987 0.05768 0.05031 -0.1119 0.0216 0.3631
12.500 1.5019 0.06023 0.05294 -0.1112 0.0208 0.3660
12.750 1.5049 0.06284 0.05561 -0.1105 0.0201 0.3694
13.000 1.5079 0.06551 0.05833 -0.1099 0.0195 0.3729
13.250 1.5107 0.06814 0.06104 -0.1093 0.0188 0.3767
13.500 1.5109 0.07121 0.06415 -0.1088 0.0182 0.3813
13.750 1.5093 0.07447 0.06748 -0.1082 0.0176 0.3868
14.000 1.5159 0.07677 0.06984 -0.1077 0.0173 0.3943
14.250 1.5232 0.07896 0.07213 -0.1074 0.0167 0.4011
14.500 1.5290 0.08141 0.07464 -0.1070 0.0162 0.4044
14.750 1.5346 0.08389 0.07718 -0.1066 0.0158 0.4053
15.000 1.5406 0.08632 0.07968 -0.1063 0.0154 0.4053
15.250 1.5463 0.08877 0.08217 -0.1060 0.0150 0.4054
15.500 1.5515 0.09128 0.08472 -0.1057 0.0146 0.4054
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