S1010 HPV airfoil (s1010-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1010 HPV airfoil (s1010-il) Reynolds number: 100,000 Max Cl/Cd: 29.89 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1010-il-100000-n5.txt Download as CSV file: xf-s1010-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1010 HPV airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.7126 0.08509 0.08025 0.0030 1.0000 0.0240
-9.250 -0.7236 0.07817 0.07346 -0.0020 1.0000 0.0238
-9.000 -0.7392 0.07043 0.06577 -0.0084 1.0000 0.0234
-8.750 -0.7561 0.06238 0.05761 -0.0124 1.0000 0.0230
-8.500 -0.7701 0.05484 0.04981 -0.0148 1.0000 0.0228
-8.250 -0.7783 0.04797 0.04250 -0.0157 1.0000 0.0229
-8.000 -0.7791 0.04185 0.03577 -0.0154 1.0000 0.0235
-7.750 -0.7720 0.03692 0.03016 -0.0145 1.0000 0.0247
-7.500 -0.7591 0.03333 0.02598 -0.0135 1.0000 0.0270
-7.250 -0.7408 0.03171 0.02423 -0.0129 1.0000 0.0297
-7.000 -0.7220 0.02909 0.02110 -0.0118 1.0000 0.0319
-6.750 -0.7014 0.02662 0.01816 -0.0108 1.0000 0.0345
-6.500 -0.6795 0.02480 0.01596 -0.0099 1.0000 0.0385
-6.250 -0.6572 0.02364 0.01473 -0.0092 1.0000 0.0429
-6.000 -0.6340 0.02206 0.01287 -0.0082 1.0000 0.0470
-5.750 -0.6114 0.02065 0.01134 -0.0073 1.0000 0.0519
-5.500 -0.5879 0.01967 0.01022 -0.0064 1.0000 0.0595
-5.250 -0.5644 0.01892 0.00943 -0.0058 1.0000 0.0705
-5.000 -0.5408 0.01818 0.00858 -0.0050 1.0000 0.0822
-4.750 -0.5170 0.01757 0.00792 -0.0043 1.0000 0.0959
-4.500 -0.4933 0.01694 0.00726 -0.0035 1.0000 0.1096
-4.250 -0.4696 0.01636 0.00666 -0.0027 1.0000 0.1244
-4.000 -0.4461 0.01577 0.00606 -0.0019 1.0000 0.1382
-3.750 -0.4226 0.01525 0.00557 -0.0011 1.0000 0.1560
-3.500 -0.3993 0.01474 0.00512 -0.0002 1.0000 0.1763
-3.250 -0.3761 0.01425 0.00466 0.0007 1.0000 0.1998
-3.000 -0.3532 0.01376 0.00429 0.0016 1.0000 0.2316
-2.750 -0.3306 0.01325 0.00397 0.0025 1.0000 0.2749
-2.500 -0.3087 0.01266 0.00369 0.0036 1.0000 0.3412
-2.250 -0.2881 0.01192 0.00345 0.0049 1.0000 0.4513
-2.000 -0.2703 0.01101 0.00335 0.0073 1.0000 0.6335
-1.750 -0.2472 0.01068 0.00355 0.0098 1.0000 0.8138
-1.500 -0.2109 0.01067 0.00359 0.0092 1.0000 0.8932
-1.250 -0.1650 0.01072 0.00354 0.0061 1.0000 0.9414
-1.000 -0.1129 0.01074 0.00347 0.0014 1.0000 0.9727
-0.750 -0.0561 0.01069 0.00333 -0.0046 1.0000 0.9962
-0.500 -0.0318 0.01064 0.00323 -0.0042 1.0000 1.0000
-0.250 -0.0159 0.01060 0.00319 -0.0021 1.0000 1.0000
0.000 0.0000 0.01059 0.00317 0.0000 1.0000 1.0000
0.250 0.0159 0.01060 0.00319 0.0021 1.0000 1.0000
0.500 0.0319 0.01063 0.00323 0.0042 1.0000 1.0000
0.750 0.0563 0.01069 0.00333 0.0045 0.9960 1.0000
1.000 0.1126 0.01074 0.00347 -0.0013 0.9729 1.0000
1.250 0.1647 0.01072 0.00354 -0.0060 0.9416 1.0000
1.500 0.2108 0.01067 0.00359 -0.0091 0.8933 1.0000
1.750 0.2470 0.01067 0.00355 -0.0098 0.8143 1.0000
2.000 0.2701 0.01101 0.00335 -0.0073 0.6335 1.0000
2.250 0.2879 0.01192 0.00345 -0.0048 0.4516 1.0000
2.500 0.3085 0.01266 0.00369 -0.0035 0.3418 1.0000
2.750 0.3304 0.01325 0.00397 -0.0025 0.2752 1.0000
3.000 0.3530 0.01376 0.00429 -0.0015 0.2317 1.0000
3.250 0.3759 0.01425 0.00465 -0.0006 0.1998 1.0000
3.500 0.3992 0.01474 0.00512 0.0003 0.1764 1.0000
3.750 0.4224 0.01525 0.00556 0.0011 0.1559 1.0000
4.000 0.4459 0.01577 0.00606 0.0019 0.1383 1.0000
4.250 0.4694 0.01636 0.00666 0.0028 0.1245 1.0000
4.500 0.4931 0.01694 0.00726 0.0036 0.1095 1.0000
4.750 0.5169 0.01756 0.00792 0.0043 0.0960 1.0000
5.000 0.5407 0.01818 0.00858 0.0050 0.0822 1.0000
5.250 0.5644 0.01892 0.00943 0.0058 0.0705 1.0000
5.500 0.5879 0.01967 0.01022 0.0064 0.0595 1.0000
5.750 0.6114 0.02066 0.01134 0.0073 0.0519 1.0000
6.000 0.6341 0.02206 0.01287 0.0082 0.0470 1.0000
6.250 0.6573 0.02364 0.01473 0.0092 0.0429 1.0000
6.500 0.6796 0.02481 0.01597 0.0098 0.0385 1.0000
6.750 0.7016 0.02663 0.01817 0.0107 0.0344 1.0000
7.000 0.7223 0.02910 0.02111 0.0118 0.0319 1.0000
7.250 0.7411 0.03173 0.02424 0.0128 0.0297 1.0000
7.500 0.7594 0.03337 0.02602 0.0135 0.0270 1.0000
7.750 0.7723 0.03698 0.03022 0.0144 0.0247 1.0000
8.000 0.7794 0.04194 0.03588 0.0153 0.0234 1.0000
8.250 0.7788 0.04802 0.04254 0.0155 0.0229 1.0000
8.500 0.7706 0.05493 0.04990 0.0146 0.0228 1.0000
8.750 0.7564 0.06258 0.05782 0.0122 0.0230 1.0000
9.000 0.7399 0.07057 0.06591 0.0081 0.0234 1.0000
9.250 0.7244 0.07832 0.07362 0.0017 0.0238 1.0000
9.500 0.7140 0.08509 0.08026 -0.0032 0.0241 1.0000
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Polar data table (+)
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