HQ 2.1/9.5 AIRFOIL (hq2195-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.1/9.5 AIRFOIL (hq2195-il) Reynolds number: 50,000 Max Cl/Cd: 37.57 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2195-il-50000-n5.txt Download as CSV file: xf-hq2195-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.1/9.5 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4581 0.12003 0.11258 -0.0202 1.0000 0.1176
-10.250 -0.4602 0.11707 0.10968 -0.0222 1.0000 0.1230
-10.000 -0.4746 0.10744 0.10008 -0.0314 1.0000 0.0682
-9.750 -0.4671 0.10353 0.09619 -0.0315 1.0000 0.0675
-9.500 -0.4630 0.09962 0.09232 -0.0322 1.0000 0.0667
-9.250 -0.4602 0.09570 0.08844 -0.0332 1.0000 0.0654
-9.000 -0.4599 0.09161 0.08443 -0.0346 1.0000 0.0637
-8.750 -0.4635 0.08710 0.08000 -0.0368 1.0000 0.0619
-8.500 -0.4716 0.08214 0.07513 -0.0399 1.0000 0.0600
-8.000 -0.5130 0.06975 0.06261 -0.0498 1.0000 0.0552
-7.750 -0.5129 0.06606 0.05888 -0.0498 1.0000 0.0548
-7.500 -0.5135 0.06234 0.05508 -0.0497 1.0000 0.0544
-7.250 -0.5130 0.05864 0.05122 -0.0495 1.0000 0.0541
-7.000 -0.5107 0.05501 0.04738 -0.0491 1.0000 0.0539
-6.750 -0.5062 0.05147 0.04357 -0.0485 1.0000 0.0537
-6.500 -0.4993 0.04809 0.03982 -0.0478 1.0000 0.0541
-6.250 -0.4894 0.04498 0.03617 -0.0470 1.0000 0.0552
-6.000 -0.4776 0.04209 0.03306 -0.0462 1.0000 0.0566
-5.750 -0.4631 0.03978 0.03058 -0.0452 1.0000 0.0580
-5.500 -0.4467 0.03735 0.02777 -0.0443 1.0000 0.0587
-5.250 -0.4286 0.03510 0.02517 -0.0434 1.0000 0.0596
-5.000 -0.4092 0.03310 0.02283 -0.0425 1.0000 0.0608
-4.750 -0.3889 0.03138 0.02080 -0.0415 1.0000 0.0630
-4.500 -0.3679 0.02994 0.01898 -0.0405 1.0000 0.0667
-4.250 -0.3467 0.02852 0.01731 -0.0394 1.0000 0.0697
-4.000 -0.3261 0.02727 0.01602 -0.0382 1.0000 0.0725
-3.750 -0.3053 0.02623 0.01487 -0.0369 1.0000 0.0762
-3.500 -0.2842 0.02544 0.01386 -0.0356 1.0000 0.0824
-3.250 -0.2638 0.02456 0.01302 -0.0347 1.0000 0.0906
-3.000 -0.2425 0.02377 0.01211 -0.0337 1.0000 0.0994
-2.750 -0.2204 0.02300 0.01135 -0.0333 1.0000 0.1168
-2.500 -0.1961 0.02205 0.01053 -0.0334 0.9997 0.1495
-2.250 -0.1685 0.01964 0.01013 -0.0348 0.9969 0.4880
-2.000 -0.1496 0.01957 0.01058 -0.0316 0.9910 0.6884
-1.750 -0.1339 0.01967 0.01089 -0.0276 0.9847 0.7863
-1.500 -0.1206 0.01959 0.01098 -0.0225 0.9784 0.8861
-1.250 -0.0573 0.01944 0.01062 -0.0286 0.9755 0.9934
-1.000 -0.0210 0.01963 0.01050 -0.0318 0.9696 1.0000
-0.750 0.0101 0.01975 0.01037 -0.0338 0.9617 1.0000
-0.500 0.0496 0.02002 0.01038 -0.0371 0.9553 1.0000
-0.250 0.0821 0.02021 0.01037 -0.0390 0.9461 1.0000
0.000 0.1208 0.02046 0.01044 -0.0418 0.9374 1.0000
0.250 0.1613 0.02068 0.01051 -0.0447 0.9274 1.0000
0.500 0.1979 0.02085 0.01057 -0.0468 0.9157 1.0000
0.750 0.2360 0.02102 0.01064 -0.0490 0.9044 1.0000
1.000 0.2778 0.02115 0.01071 -0.0518 0.8942 1.0000
1.250 0.3157 0.02127 0.01081 -0.0538 0.8830 1.0000
1.500 0.3492 0.02141 0.01094 -0.0549 0.8710 1.0000
1.750 0.3834 0.02152 0.01105 -0.0560 0.8591 1.0000
2.000 0.4190 0.02158 0.01115 -0.0573 0.8474 1.0000
2.250 0.4561 0.02158 0.01121 -0.0586 0.8357 1.0000
2.500 0.4888 0.02160 0.01130 -0.0591 0.8220 1.0000
2.750 0.5204 0.02160 0.01137 -0.0593 0.8072 1.0000
3.000 0.5520 0.02156 0.01144 -0.0594 0.7917 1.0000
3.250 0.5788 0.02159 0.01158 -0.0587 0.7730 1.0000
3.500 0.6077 0.02154 0.01164 -0.0581 0.7538 1.0000
3.750 0.6386 0.02139 0.01163 -0.0577 0.7341 1.0000
4.000 0.6644 0.02137 0.01173 -0.0566 0.7095 1.0000
4.250 0.6912 0.02129 0.01177 -0.0556 0.6826 1.0000
4.500 0.7166 0.02124 0.01186 -0.0543 0.6505 1.0000
4.750 0.7426 0.02114 0.01181 -0.0529 0.6128 1.0000
5.000 0.7684 0.02107 0.01168 -0.0513 0.5681 1.0000
5.250 0.7934 0.02122 0.01161 -0.0497 0.5192 1.0000
5.500 0.8157 0.02171 0.01189 -0.0480 0.4712 1.0000
5.750 0.8357 0.02243 0.01240 -0.0465 0.4259 1.0000
6.000 0.8545 0.02323 0.01308 -0.0449 0.3831 1.0000
6.250 0.8723 0.02410 0.01386 -0.0434 0.3408 1.0000
6.500 0.8890 0.02505 0.01475 -0.0418 0.2961 1.0000
6.750 0.9042 0.02614 0.01569 -0.0402 0.2484 1.0000
7.000 0.9189 0.02744 0.01676 -0.0386 0.2044 1.0000
7.250 0.9343 0.02891 0.01802 -0.0372 0.1686 1.0000
7.500 0.9504 0.03047 0.01943 -0.0359 0.1434 1.0000
7.750 0.9674 0.03205 0.02098 -0.0348 0.1237 1.0000
8.000 0.9849 0.03367 0.02257 -0.0338 0.1086 1.0000
8.250 1.0038 0.03534 0.02432 -0.0328 0.0966 1.0000
8.500 1.0236 0.03712 0.02623 -0.0319 0.0870 1.0000
8.750 1.0441 0.03909 0.02817 -0.0312 0.0807 1.0000
9.000 1.0652 0.04120 0.03066 -0.0304 0.0742 1.0000
9.250 1.0827 0.04315 0.03268 -0.0295 0.0690 1.0000
9.500 1.1025 0.04581 0.03559 -0.0288 0.0656 1.0000
9.750 1.1182 0.04878 0.03902 -0.0277 0.0629 1.0000
10.000 1.1290 0.05166 0.04226 -0.0263 0.0603 1.0000
10.250 1.1377 0.05422 0.04503 -0.0250 0.0576 1.0000
10.500 1.1479 0.05707 0.04787 -0.0242 0.0551 1.0000
10.750 1.1418 0.06054 0.05190 -0.0219 0.0541 1.0000
11.000 1.1314 0.06416 0.05591 -0.0195 0.0535 1.0000
11.250 1.1169 0.06806 0.06015 -0.0177 0.0532 1.0000
11.500 1.0990 0.07239 0.06476 -0.0168 0.0530 1.0000
11.750 1.0782 0.07732 0.06995 -0.0171 0.0529 1.0000
12.000 1.0553 0.08299 0.07581 -0.0186 0.0531 1.0000
12.250 1.0302 0.08968 0.08268 -0.0217 0.0533 1.0000
12.500 1.0044 0.09754 0.09068 -0.0263 0.0537 1.0000
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Polar data table (+)
Polar graphs
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