HQ 1.0/9 AIRFOIL (hq109-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.0/9 AIRFOIL (hq109-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.63 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq109-il-1000000-n5.txt Download as CSV file: xf-hq109-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.8455 0.05701 0.05541 -0.0317 1.0000 0.0019
-11.500 -0.9217 0.03940 0.03732 -0.0428 1.0000 0.0018
-11.250 -0.9249 0.03758 0.03540 -0.0411 1.0000 0.0019
-11.000 -0.9227 0.03533 0.03301 -0.0401 1.0000 0.0019
-10.750 -0.9303 0.03120 0.02852 -0.0386 1.0000 0.0020
-10.500 -0.9245 0.02847 0.02552 -0.0374 1.0000 0.0020
-10.250 -0.9144 0.02612 0.02291 -0.0363 1.0000 0.0020
-10.000 -0.9001 0.02427 0.02084 -0.0354 1.0000 0.0021
-9.750 -0.8833 0.02273 0.01910 -0.0345 1.0000 0.0022
-9.500 -0.8664 0.02108 0.01722 -0.0336 1.0000 0.0022
-9.250 -0.8482 0.01960 0.01554 -0.0326 1.0000 0.0023
-9.000 -0.8284 0.01840 0.01414 -0.0318 1.0000 0.0024
-8.750 -0.8079 0.01733 0.01292 -0.0309 1.0000 0.0024
-8.500 -0.7873 0.01630 0.01174 -0.0300 1.0000 0.0025
-8.250 -0.7663 0.01540 0.01070 -0.0291 1.0000 0.0026
-8.000 -0.7436 0.01467 0.00987 -0.0284 0.9996 0.0028
-7.750 -0.7129 0.01415 0.00927 -0.0294 0.9941 0.0029
-7.500 -0.6821 0.01346 0.00847 -0.0304 0.9886 0.0030
-7.250 -0.6507 0.01274 0.00766 -0.0316 0.9824 0.0031
-7.000 -0.6203 0.01167 0.00644 -0.0326 0.9738 0.0037
-6.750 -0.5891 0.01119 0.00587 -0.0336 0.9636 0.0041
-6.500 -0.5590 0.01077 0.00540 -0.0342 0.9505 0.0046
-6.250 -0.5313 0.01042 0.00496 -0.0343 0.9337 0.0051
-6.000 -0.5052 0.01012 0.00456 -0.0339 0.9169 0.0055
-5.750 -0.4795 0.00987 0.00422 -0.0335 0.9024 0.0057
-5.500 -0.4542 0.00945 0.00369 -0.0330 0.8895 0.0070
-5.250 -0.4282 0.00919 0.00339 -0.0327 0.8774 0.0084
-5.000 -0.4017 0.00898 0.00309 -0.0325 0.8668 0.0095
-4.750 -0.3751 0.00876 0.00280 -0.0322 0.8569 0.0116
-4.500 -0.3486 0.00853 0.00255 -0.0320 0.8476 0.0163
-4.250 -0.3218 0.00830 0.00234 -0.0318 0.8383 0.0255
-4.000 -0.2949 0.00811 0.00214 -0.0317 0.8290 0.0343
-3.750 -0.2678 0.00796 0.00197 -0.0315 0.8194 0.0420
-3.500 -0.2406 0.00782 0.00180 -0.0314 0.8091 0.0504
-3.250 -0.2136 0.00762 0.00164 -0.0313 0.7989 0.0674
-3.000 -0.1867 0.00739 0.00148 -0.0312 0.7891 0.0954
-2.750 -0.1600 0.00715 0.00133 -0.0311 0.7790 0.1336
-2.500 -0.1327 0.00695 0.00120 -0.0310 0.7696 0.1681
-2.000 -0.0781 0.00662 0.00100 -0.0309 0.7531 0.2296
-1.750 -0.0521 0.00618 0.00086 -0.0308 0.7417 0.3290
-1.500 -0.0261 0.00583 0.00076 -0.0307 0.7275 0.4228
-1.250 0.0010 0.00568 0.00070 -0.0306 0.7143 0.4683
-1.000 0.0277 0.00545 0.00066 -0.0305 0.7032 0.5376
-0.750 0.0548 0.00535 0.00065 -0.0303 0.6896 0.5838
-0.500 0.0821 0.00532 0.00064 -0.0302 0.6742 0.6116
-0.250 0.1097 0.00530 0.00064 -0.0301 0.6605 0.6336
0.000 0.1374 0.00531 0.00064 -0.0300 0.6470 0.6500
0.250 0.1651 0.00532 0.00065 -0.0300 0.6334 0.6643
0.500 0.1927 0.00536 0.00067 -0.0299 0.6164 0.6772
0.750 0.2202 0.00541 0.00069 -0.0298 0.5960 0.6901
1.000 0.2476 0.00547 0.00072 -0.0297 0.5746 0.7039
1.250 0.2748 0.00555 0.00076 -0.0296 0.5500 0.7176
1.500 0.3016 0.00570 0.00083 -0.0294 0.5148 0.7285
2.000 0.3548 0.00611 0.00099 -0.0290 0.4318 0.7474
2.250 0.3808 0.00639 0.00111 -0.0288 0.3808 0.7569
2.500 0.4062 0.00678 0.00126 -0.0285 0.3114 0.7670
2.750 0.4326 0.00701 0.00140 -0.0283 0.2751 0.7779
3.000 0.4590 0.00721 0.00154 -0.0281 0.2474 0.7890
3.250 0.4857 0.00738 0.00167 -0.0280 0.2273 0.8005
3.500 0.5122 0.00755 0.00183 -0.0278 0.2044 0.8123
3.750 0.5387 0.00771 0.00197 -0.0275 0.1862 0.8250
4.000 0.5646 0.00792 0.00214 -0.0273 0.1609 0.8389
4.500 0.6139 0.00856 0.00259 -0.0263 0.0915 0.8736
4.750 0.6376 0.00883 0.00285 -0.0255 0.0660 0.9016
5.000 0.6654 0.00902 0.00310 -0.0256 0.0499 0.9546
5.250 0.7025 0.00933 0.00337 -0.0278 0.0374 1.0000
5.500 0.7283 0.00963 0.00363 -0.0276 0.0285 1.0000
5.750 0.7537 0.00998 0.00392 -0.0273 0.0194 1.0000
6.000 0.7789 0.01035 0.00425 -0.0269 0.0124 1.0000
6.250 0.8041 0.01073 0.00462 -0.0266 0.0075 1.0000
6.500 0.8291 0.01112 0.00501 -0.0262 0.0049 1.0000
6.750 0.8544 0.01148 0.00540 -0.0258 0.0040 1.0000
7.000 0.8794 0.01186 0.00582 -0.0254 0.0036 1.0000
7.250 0.9041 0.01229 0.00629 -0.0250 0.0031 1.0000
7.500 0.9282 0.01280 0.00686 -0.0245 0.0027 1.0000
7.750 0.9514 0.01346 0.00761 -0.0238 0.0024 1.0000
8.000 0.9732 0.01432 0.00860 -0.0229 0.0022 1.0000
8.250 0.9962 0.01495 0.00934 -0.0222 0.0022 1.0000
8.500 1.0193 0.01552 0.00997 -0.0216 0.0022 1.0000
8.750 1.0419 0.01616 0.01069 -0.0210 0.0021 1.0000
9.000 1.0639 0.01684 0.01145 -0.0203 0.0020 1.0000
9.250 1.0861 0.01746 0.01216 -0.0196 0.0019 1.0000
9.500 1.1067 0.01829 0.01309 -0.0187 0.0018 1.0000
9.750 1.1268 0.01913 0.01404 -0.0178 0.0018 1.0000
10.000 1.1452 0.02017 0.01521 -0.0167 0.0017 1.0000
10.250 1.1628 0.02123 0.01640 -0.0155 0.0017 1.0000
10.500 1.1792 0.02239 0.01772 -0.0142 0.0016 1.0000
10.750 1.1950 0.02351 0.01898 -0.0128 0.0016 1.0000
11.000 1.2081 0.02484 0.02047 -0.0112 0.0016 1.0000
11.250 1.2195 0.02622 0.02201 -0.0095 0.0015 1.0000
11.500 1.2274 0.02779 0.02375 -0.0073 0.0015 1.0000
11.750 1.2325 0.02908 0.02517 -0.0047 0.0015 1.0000
12.000 1.2343 0.03048 0.02671 -0.0019 0.0014 1.0000
12.250 1.2281 0.03261 0.02903 0.0011 0.0014 1.0000
12.500 1.2227 0.03486 0.03145 0.0033 0.0014 1.0000
12.750 1.2233 0.03676 0.03346 0.0045 0.0014 1.0000
13.000 1.2122 0.04005 0.03694 0.0054 0.0014 1.0000
13.250 1.2018 0.04366 0.04072 0.0054 0.0014 1.0000
13.500 1.1976 0.04687 0.04404 0.0047 0.0013 1.0000
13.750 1.1888 0.05107 0.04838 0.0032 0.0013 1.0000
14.000 1.1537 0.06008 0.05766 -0.0015 0.0014 1.0000
14.250 1.1374 0.06729 0.06501 -0.0062 0.0014 1.0000
14.500 1.1036 0.07938 0.07731 -0.0142 0.0014 1.0000
14.750 1.0891 0.08795 0.08598 -0.0195 0.0014 1.0000
15.000 1.0188 0.10967 0.10794 -0.0318 0.0015 1.0000
15.250 0.9974 0.11993 0.11825 -0.0372 0.0015 1.0000
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