SARATOV AIRFOIL (saratov-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SARATOV AIRFOIL (saratov-il) Reynolds number: 200,000 Max Cl/Cd: 77.9 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-saratov-il-200000-n5.txt Download as CSV file: xf-saratov-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0292 0.09726 0.09159 -0.0935 0.5972 0.0371
-9.500 -0.0232 0.09459 0.08886 -0.0945 0.5921 0.0374
-9.250 -0.0172 0.09189 0.08614 -0.0955 0.5878 0.0376
-9.000 -0.0142 0.08887 0.08309 -0.0969 0.5841 0.0387
-8.750 -0.0194 0.08490 0.07914 -0.0996 0.5815 0.0401
-8.500 -0.0117 0.08253 0.07673 -0.0999 0.5781 0.0406
-8.250 -0.0012 0.08075 0.07491 -0.1001 0.5750 0.0410
-8.000 0.0068 0.07867 0.07283 -0.1005 0.5723 0.0413
-7.750 0.0166 0.07700 0.07114 -0.1007 0.5696 0.0420
-7.500 0.0258 0.07546 0.06957 -0.1008 0.5669 0.0429
-7.250 0.0322 0.07378 0.06787 -0.1009 0.5648 0.0440
-7.000 0.0392 0.07150 0.06557 -0.1022 0.5629 0.0446
-6.750 0.0473 0.06886 0.06290 -0.1040 0.5611 0.0449
-6.500 0.0570 0.06602 0.06002 -0.1064 0.5595 0.0452
-6.250 0.0688 0.06295 0.05693 -0.1094 0.5580 0.0456
-6.000 0.0826 0.05960 0.05355 -0.1131 0.5564 0.0461
-5.500 0.1429 0.03140 0.02451 -0.1570 0.5540 0.0511
-5.250 0.1756 0.02881 0.02169 -0.1614 0.5520 0.0527
-5.000 0.2058 0.02746 0.02021 -0.1637 0.5501 0.0544
-4.750 0.2369 0.02588 0.01841 -0.1663 0.5482 0.0564
-4.500 0.2679 0.02447 0.01677 -0.1686 0.5466 0.0582
-4.250 0.2980 0.02343 0.01552 -0.1701 0.5450 0.0598
-4.000 0.3279 0.02260 0.01448 -0.1714 0.5437 0.0614
-3.750 0.3575 0.02189 0.01357 -0.1724 0.5425 0.0629
-3.500 0.3859 0.02170 0.01336 -0.1727 0.5414 0.0656
-3.250 0.4159 0.02095 0.01255 -0.1738 0.5402 0.0702
-3.000 0.4464 0.01993 0.01137 -0.1753 0.5390 0.0754
-2.750 0.4770 0.01886 0.01019 -0.1768 0.5379 0.0839
-2.500 0.5047 0.01910 0.01065 -0.1766 0.5368 0.0998
-2.250 0.5360 0.01759 0.00872 -0.1785 0.5358 0.1268
-2.000 0.5637 0.01787 0.00901 -0.1783 0.5347 0.1355
-1.750 0.5921 0.01773 0.00873 -0.1786 0.5338 0.1429
-1.500 0.6191 0.01818 0.00924 -0.1781 0.5328 0.1475
-1.250 0.6478 0.01778 0.00862 -0.1786 0.5320 0.1527
-1.000 0.6760 0.01758 0.00827 -0.1788 0.5311 0.1567
-0.750 0.7028 0.01800 0.00880 -0.1783 0.5303 0.1599
-0.500 0.7300 0.01827 0.00910 -0.1781 0.5296 0.1638
-0.250 0.7582 0.01803 0.00873 -0.1783 0.5289 0.1672
0.000 0.7864 0.01782 0.00835 -0.1785 0.5282 0.1705
0.250 0.8141 0.01781 0.00829 -0.1785 0.5276 0.1736
0.500 0.8414 0.01798 0.00851 -0.1784 0.5270 0.1763
0.750 0.8690 0.01802 0.00854 -0.1784 0.5264 0.1784
1.000 0.8969 0.01799 0.00845 -0.1784 0.5258 0.1798
1.250 0.9243 0.01793 0.00837 -0.1784 0.5253 0.1813
1.500 0.9515 0.01789 0.00833 -0.1783 0.5246 0.1828
1.750 0.9786 0.01788 0.00833 -0.1782 0.5239 0.1844
2.000 1.0053 0.01788 0.00834 -0.1780 0.5226 0.1859
2.250 1.0317 0.01788 0.00835 -0.1777 0.5207 0.1874
2.500 1.0580 0.01788 0.00839 -0.1774 0.5185 0.1889
2.750 1.0844 0.01793 0.00851 -0.1771 0.5167 0.1907
3.000 1.1110 0.01803 0.00867 -0.1769 0.5155 0.1927
3.250 1.1375 0.01812 0.00883 -0.1767 0.5139 0.1953
3.500 1.1641 0.01819 0.00892 -0.1764 0.5118 0.1986
3.750 1.1910 0.01830 0.00901 -0.1762 0.5099 0.2019
4.000 1.2180 0.01847 0.00921 -0.1760 0.5087 0.2049
4.250 1.2433 0.01861 0.00952 -0.1756 0.5075 0.2079
4.500 1.2683 0.01875 0.00981 -0.1751 0.5058 0.2116
4.750 1.2932 0.01888 0.01006 -0.1746 0.5035 0.2161
5.000 1.3182 0.01900 0.01031 -0.1740 0.5012 0.2210
5.250 1.3434 0.01918 0.01064 -0.1736 0.4993 0.2264
5.500 1.3688 0.01931 0.01088 -0.1731 0.4970 0.2341
5.750 1.3945 0.01946 0.01113 -0.1726 0.4940 0.2413
6.000 1.4201 0.01964 0.01139 -0.1721 0.4912 0.2508
6.250 1.4417 0.01988 0.01187 -0.1710 0.4877 0.2570
6.500 1.4647 0.02006 0.01222 -0.1701 0.4842 0.2667
6.750 1.4881 0.02021 0.01250 -0.1692 0.4805 0.2750
7.000 1.5122 0.02015 0.01246 -0.1683 0.4752 0.2846
7.250 1.5292 0.02014 0.01267 -0.1662 0.4650 0.2950
7.500 1.5473 0.02008 0.01275 -0.1643 0.4522 0.3019
7.750 1.5643 0.02008 0.01289 -0.1623 0.4328 0.3100
8.000 1.5534 0.02047 0.01270 -0.1553 0.3237 0.3129
8.250 1.5194 0.02280 0.01459 -0.1455 0.2470 0.3135
8.500 1.4924 0.02540 0.01694 -0.1382 0.1974 0.3148
8.750 1.4796 0.02758 0.01906 -0.1334 0.1789 0.3189
9.000 1.4714 0.02974 0.02124 -0.1296 0.1677 0.3215
9.250 1.4633 0.03215 0.02370 -0.1265 0.1590 0.3235
9.500 1.4591 0.03454 0.02616 -0.1240 0.1510 0.3265
9.750 1.4528 0.03737 0.02904 -0.1219 0.1436 0.3299
10.000 1.4505 0.04006 0.03179 -0.1203 0.1359 0.3330
10.250 1.4477 0.04292 0.03472 -0.1190 0.1283 0.3349
10.500 1.4477 0.04562 0.03750 -0.1179 0.1215 0.3376
10.750 1.4471 0.04844 0.04035 -0.1169 0.1130 0.3413
11.000 1.4484 0.05109 0.04306 -0.1160 0.1033 0.3447
11.250 1.4487 0.05390 0.04591 -0.1152 0.0922 0.3471
11.500 1.4466 0.05699 0.04894 -0.1143 0.0752 0.3500
11.750 1.4418 0.06041 0.05222 -0.1135 0.0560 0.3529
12.000 1.4373 0.06379 0.05545 -0.1125 0.0401 0.3557
12.250 1.4373 0.06670 0.05832 -0.1118 0.0320 0.3587
12.500 1.4405 0.06929 0.06093 -0.1110 0.0275 0.3631
12.750 1.4443 0.07186 0.06352 -0.1104 0.0250 0.3671
13.000 1.4497 0.07429 0.06603 -0.1099 0.0234 0.3709
13.250 1.4556 0.07668 0.06851 -0.1094 0.0219 0.3746
13.500 1.4607 0.07921 0.07112 -0.1089 0.0207 0.3765
13.750 1.4645 0.08194 0.07392 -0.1085 0.0195 0.3774
14.000 1.4686 0.08468 0.07674 -0.1082 0.0186 0.3782
14.250 1.4745 0.08717 0.07934 -0.1079 0.0178 0.3793
14.500 1.4792 0.08985 0.08211 -0.1077 0.0172 0.3806
14.750 1.4837 0.09256 0.08492 -0.1074 0.0166 0.3821
15.000 1.4880 0.09531 0.08776 -0.1073 0.0161 0.3833
15.250 1.4920 0.09811 0.09065 -0.1071 0.0156 0.3842
15.500 1.4953 0.10100 0.09361 -0.1070 0.0152 0.3848
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